Vehicle aerodynamic sensing technology based on surface distributed pressure
SUN Rong , LI Linkai etc.
 doi: 10.11729/syltlx20230008
[Abstract](11) [FullText HTML](3) [PDF 10061KB](2)
In the environment of large crosswind or wind shear, the aircraft, high-speed rail, trucks, ships and other vehicles may rollover, which may cause safety accidents. For the crosswind or wind shear phenomenon, the existing technology mainly studies, monitors and gives early warning from the atmospheric macro environment, and often cannot accurately perceive the random aerodynamic load or sudden flow around the vehicle itself. We take the van truck as the research object, and propose a real-time sensing method of on-board aerodynamic force/moment based on the distributed pressure information on the surface. By measuring the distributed pressure on the body surface, the rolling moment coefficient of the characteristic section is obtained, so as to judge the rolling moment of the truck in the crosswind environment. The wind tunnel test results show that the rolling moment coefficient of the pressure tap section located at 0.15 L of the vehicle body is highly related to the rolling moment coefficient of the whole vehicle model, which can be used as a characteristic section to sense and judge its rolling moment, and we also use multiple section fitting to sense the rolling moment, which is more accurate than single section fitting, but needs to monitor the pressure at more positions of the body surface.
Applicability analysis of Sivells method in nozzle design with high Mach number and low total pressure
LI Zhenqian , SHI Yilei etc.
 doi: 10.11729/syltlx20220045
[Abstract](71) [FullText HTML](26) [PDF 8203KB](21)
At present, the Sivells method is widely used for the design of the inviscid hypersonic axisymmetric nozzle contour. And then, the nozzle contour viscous correction is performed by solving the axisymmetric momentum equation. This design procedure is validated by nozzles in conventional hypersonic wind tunnels and shock wind tunnels, which are operated under high Mach number and high total pressure conditions. Meanwhile, there are few validation studies of this procedure under high Mach number and low total pressure conditions. In this study, the nozzle design procedure based on the Sivells method is used for Mach 6, 8, 10, and 12 nozzle contour design under the low total pressure condition. Furthermore, in order to analyze nozzle flowfields, numerical simulation and wind tunnel experiment are carried out. It can be found that, the flowfields in Mach 6 nozzle and Mach 8 nozzle are consistent with expectation and the jet flowfields are so good that are suitable for test. In contrast, there are some over-expanded areas in the flowfields of Mach 10 nozzle and Mach 12 nozzle, which results in higher Mach number than expectation in those areas. The jet flowfield quality of Mach 10 nozzle is better than that of Mach 12 nozzle. It can be concluded that, under the condition of low total pressure, the Sivells method still works well for Mach 6 nozzle and Mach 8 nozzle design. Meanwhile, the method is less effective when applied to the Mach 10 nozzle and Mach 12 nozzle design.
Experimental study and statistical analysis of flow field pulsation of spiked cylinder
WANG Yifan , QIN Qihao etc.
 doi: 10.11729/syltlx20220078
[Abstract](61) [FullText HTML](15) [PDF 7875KB](8)
The cylinder with a pointed spike and the spiked cylinder with aerodome were investigated under the condition of Ma = 2.2 incoming flow using a direct-connected wind tunnel and a high-speed schlieren system. The experimental results were statistically analyzed to investigate the unsteady flow field pulsation of the spiked cylinder under supersonic incoming flow. Based on the transient data, the typical structure and evolution of the flow field were first interpreted. The convergence of the residuals was then used to assess the dependability of the statistical results. Finally, the pulsation characteristics of the flow field were further analyzed in terms of the time-averaged and pulsating flow fields. The results show that there is unsteady pulsation in the spiked cylinder flow field under the condition of the supersonic incoming flow, which is more intense in the case of the cylinder with a pointed spike and attenuated in the case of the spiked cylinder with aerodome, demonstrating the suppression of unsteady pulsation in the flow field by the aerodome.
Infrared thermogram measurement experiment of hypersonic boundary-layer transition of a lifting body
CHEN Jiufen , XU Yang etc.
 doi: 10.11729/syltlx20220030
[Abstract](70) [FullText HTML](44) [PDF 8806KB](18)
For a lifting body model, the boundary layer transition infrared thermogram measurement experiment was carried out in the conventional hypersonic wind tunnel, and the influence of different unit Reynolds number and Mach number on the lifting body boundary layer transition was studied, which was compared with the calculation results of the eN method. The length of the experimental model is 800 mm, the unit Reynolds number is 0.46×107~3.94×107 m–1, the Mach number is 5~8, and the angle of attack is 0°. The transition position and transition front of the boundary layer on the surface of the model are obtained by the large-area infrared thermogram technology. The analysis of the experimental results shows that there are crossflow instability and the second mode transition in the boundary layer of the lifting body. As the unit Reynolds number increases, the crossflow transition effect increases, the temperature rise on the lower and upper surfaces of the model increases, the transition front moves forward, and the transition area expands; as the Mach number increases, the crossflow transition effect gradually weakens and the transition position moves downstream, and the transition area significantly shrinks back. Moreover, the transition N factor at different Mach numbers and unit Reynolds numbers are relatively close, but the N factors of the upper and lower surfaces are different. The lower surface is about 6, and the upper surface is about 2.5. The high-frequency second mode transition occurs in the side edge at high unit Reynolds numbers.
Pressure sensitive paint measurement correction method based on surface spline interpolation
JING Zhiwei , WANG Libo etc.
 doi: 10.11729/syltlx20220027
[Abstract](58) [FullText HTML](35) [PDF 6692KB](3)
The PSP(Pressure Sensitive Paint) measurements correction after the wind tunnel test is often implemented through the least square method, and it tends to neglect the chordwise and spanwise flow characteristics on the wing. By employing the IPS (Infinite Plate Spline) technique, a hybrid correction method and process for the PSP test results was presented. A full-span airplane model, with PSI (Pressure Scanner Instrument) and PSP on the upper and lower surfaces of the wing, was utilized to carry out the PSP test and PSI test simultaneously in a transonic wind tunnel with the 2.4 m test section. The pressure measurements were conducted at Ma = 0.735 and in the angle of attack range from −6.38° to 10.59°. Test results indicate that the PSP data demonstrate a good agreement with PSI data. However, the PSP test system with only one camera shows a poor capacity to capture the aerodynamic field at the wing leading edge. The hybrid correction method for PSP results has proven to an effective approach, and the corrected data reveal that the hybrid correction can better deal with the pressure distribution characteristics of the full wing.
Experimental study on RP3 aviation kerosene oblique detonation engine
HAN Xin , ZHANG Wenshuo etc.
 doi: 10.11729/syltlx20220090
[Abstract](1087) [FullText HTML](217) [PDF 9313KB](35)
The oblique detonation engine has great potential application in high flight Mach number airbreathing vehicles because of its higher thermodynamic efficiency and smaller size. The research about the oblique detonation engine is renewed all over the world in recent years. However, all of the oblique detonation experiments are conducted with hydrogen fuel or ethylene. There is no experimental result about the kerosene oblique detonation. In order to examine the application feasibility of kerosene oblique detonation engine, the experimental study on the liquid RP3 aviation kerosene oblique detonation engine is conducted in JF-12 shock tunnel and the test time is about 50ms. The difficult issue for the initiation of kerosene oblique detonation is that the ignition delay time of kerosene-air is too long and the autoignition cannot occur in the combustor. A new forced detonation initiation method is put forth to deal with this key issue. The total temperature of JF-12 shock tunnel is 3800 K and the global equivalence ratio is 0.9, which replicates Mach 9 flight-equivalent condition. The steady-state oblique detonation is obtained successfully during the experiments, which demonstrates the application feasibility of the kerosene oblique detonation engine.
Pressure fluctuation experiments of hypersonic boundary-layer on a 7-degree half-angle sharp cone
CHEN Jiufen , XU Yang etc.
 doi: 10.11729/syltlx20210054
[Abstract](78) [FullText HTML](27) [PDF 11507KB](16)
In a conventional hypersonic wind-tunnel, pressure fluctuations of the boundary layer on a 7-degree half-angle sharp cone are measured by surface sensors and are analyzed by the linear stability theory. The influences of unit Reynolds numbers and Mach number on the stability and transition position of the boundary layer are studied. The length of the test model is 800 mm and the radius of the head is 0.05 mm. Test unit Reynolds numbers range from 0.49×10 7m–1 to 2.45×107 m–1. Test Mach numbers range from 5 to 8. The angle of attack is 0°. The transition position and the energy spectrum distribution of the disturbance wave in the boundary layer are obtained by the quantitative infrared thermography and high frequency surface pressure fluctuation measurement techniques. The frequency and growth rate of the most unstable wave are analyzed by using the linear stability theory. The experimental results show that the fluctuating pressure signal with obvious characteristics of the unstable wave spectrum can be measured in the transition region. The frequency of the pressure fluctuation is close to that of the second mode instability analyzed by the linear stability theory, and the amplitude variation trend is also similar to that of the theoretical analysis. With the increase of the unit Reynolds number, the instability appears earlier, the dominant frequency is increased, and the transition onset moves forward. The unstable wave in the boundary layer contains the first and second modes. When the free-stream Mach number is equal to 5, the transition is caused by the first mode, and when the Mach number is above 6, the transition is attributed to the second mode.
Experimental research on the influence of turbulence intensity on boundary layer transition in Mach 3 supersonic flow
LI Meng , ZHAO Huiyong etc.
 doi: 10.11729/syltlx20220087
[Abstract](74) [FullText HTML](26) [PDF 9099KB](18)
There is still a shortage of the experimental research of boundary layer transition in compressible flows nowadays due to the difficulty in measuring the turbulence intensity. Aiming at studying the influence of the turbulence intensity on supersonic boundary layer transition, a plate model is tested in a blow-down facility (FL-24y of CARDC) at Mach 3. The turbulence intensity of the flow is changed by adjusting the arrangements in the stabilization section of the wind tunnel, which covers a range from 0.82% to 1.63%. The turbulence intensity is measured by interferometric Rayleigh scattering, while the boundary layer transition is derived by infrared thermography. The CFD simulation of the plate model transition is conducted based on the γ-Reθ transition model. The results show that the transition onset position (Fonset) and transition end position (Flength) obtained by the experiment and the simulation agree well, with the maximum relative error coefficient of 2% in Fonset and of 5% in Flength, which provides support to gain a deeper insight into the boundary layer transition mechanism in supersonic flows.
Study on evaporation heat transfer characteristics of sessile droplets based on temperature measurement of double layer temperature sensitive paint
LI Bingjie , ZHANG Shulei etc.
 doi: 10.11729/syltlx20220132
[Abstract](24) [FullText HTML](5) [PDF 6787KB](4)
As a new non-contact temperature measurement method, temperature sensitive paint has the advantages of low cost and fast response. In this paper, a temperature measurement technology based on double layer temperature sensitive paint was used to study the heat transfer characteristics of sessile droplet evaporation. The temperature distributions at the contact surface between the droplet and the heating substrate and at the back of the substrate were obtained by measuring the temperature with a double-layer temperature sensitive paint. A one-dimensional unsteady inverse heat conduction model was established to obtain the heat flux distribution at the interface between the droplet and the heating substrate. The results show that the droplet vaporization process can be divided into three stages: initial heating stage, convection unit evaporation stage and film evaporation stage. In the initial heating stage, the heat flux increases rapidly. In the convection unit evaporation stage, the heat flux decreases gradually and remains basically unchanged. In the film evaporation stage, the heat flux first increases, and then decreases rapidly as the droplet almost completely evaporates. The reliability of the experimental method is verified by checking the heat quantity of droplet evaporation. The research results in this paper are helpful to broaden the experimental measurement method of heat flux during phase change heat transfer.
Visualization experiment of wave dynamics in pressure oscillation tube
GUO Jiangtao , ZHOU Yihui etc.
 doi: 10.11729/syltlx20220039
[Abstract](15) [FullText HTML](4) [PDF 18534KB](2)
Gas Wave Refrigerator(GWR) is a kind of equipment with strong adaptability to complex working conditions. It has the advantages of high refrigeration efficiency, and can work with liquid. The pressure oscillation tube is the core part of GWR. A visual flow field measurement platform was designed to study the wave motion inside the pressure oscillation tube. The flow field splices and the schlieren technique are used to obtain the density gradient field in the tube, and the results are compared with the theoretical calculation of the two-dimensional Euler equation. The deviation between the experiment and the simulation is 3.2%. Based on the above method, experiments with different pressure ratios and rotational speeds were carried out. The experimental results show that the shock Mach number can be increased by increasing the pressure ratio or speed. When the pressure ratio increases from 1.5 to 3.0, the intensity of the shock wave and expansion wave increases significantly. When the rotational speed increases from 800 r/min to 2400 r/min, the motion path of the expansion wave system gradually bends towards the nozzle, which prolongs the time of the expansion wave at the nozzle.
Droplet spreading on an oblique surface
LU Jie , LI Yalei etc.
 doi: 10.11729/syltlx20220012
[Abstract](138) [FullText HTML](36) [PDF 7340KB](3)
Droplet spreading on a surface is ubiquitous in a variety of applications including aerospace, industry, and agriculture. Majority of these impacts are oblique, while previous studies focused on orthogonal impacts. Oblique impacts cannot be understood directly by previous theories and/or models. Evolution of film formation following a droplet impacting an oblique surface is investigated experimentally. Evolution of the film shape is obtained under various inclination angles and Weber numbers. Based on a new theory of droplet spreading on oblique surfaces, evolution of the film shape is analyzed. It is found that the film shape at small inclination angles can be predicted reasonably, but the error between the predicted maximum lamella width along the inclination direction and the experimental data is relatively big at large inclination angles since the length of the upstream lamella is assumed as a constant in the theory. Modifications of the theory including more detailed analysis of the length of the upstream lamella lead to an analytical model which permits the theoretical determination of the maximum lamella shape. It is shown that the error between the predicted results and the experimental results can be reduced from 61.8% by the previous theory to 3.2%. The model provides a better prediction on the lamella shape at large inclination angles, and a more concise and accurate theoretical tool for engineering applications.
Wind tunnel test technique of continuous varying Mach number for air-breathing vehicle
ZHOU Jian , ZHANG Jiang etc.
 doi: 10.11729/syltlx20210189
[Abstract](96) [FullText HTML](21) [PDF 9642KB](0)
To study the start/unstart phenomenon of the air-breathing vehicle inlet caused by acceleration or deceleration, which also bring the problem of aerodynamic mutation on vehicle, the test technique of continuous varying Mach number was performed in the 1.2 m supersonic wind tunnel based on the flow mechanism of the 2D wedge shock wave. By developing the shock wave generator system, continuous varying Mach number was realized successfully in one wind tunnel test process. And it has also been confirmed that the technical method can make Mach number vary simply and quickly with high quality and precision. Through the flow-field calibration, the quality of the instantaneous flow-field in variable Mach number region meets the standards of GJB eligibly, and thus the field can be used for force and pressure test compliantly. In addition, the test of inlet starting characteristics was carried out and the dynamic process and critical state from start to unstart were captured, which indicates that the test results agree with the numerical simulation accurately. The test technique could provide effective support for supersonic air-breathing vehicle in aerodynamic performance prediction and study.
Evolution of high-speed cavity flow based on PIV technology
WU Jifei , ZHOU Fangqi etc.
 doi: 10.11729/syltlx20210144
[Abstract](62) [FullText HTML](33) [PDF 8883KB](4)
In cavity structure, complex flows and high-intensity noises appear under the high-speed condition, seriously affecting the aerodynamic characteristics and structural safety of the aircraft. Through the methods of the PIV technology and dynamic pressure measurement, the cavity with a length-depth ratio of 3 to 10 is experimentally investigated in the range of Mach number 0.4 to 0.8. The influences of the length-depth ratio and Mach number on the flow field structure in the cavity are emphatically analyzed, and the correlations between the noise intensity and the flow velocity are revealed. The results show that: as the length-depth ratio increases, the thickness of the shear layer in the cavity increases rapidly and expands into the cavity, leading the impact position on the cavity to move down from the back wall to the bottom, and causing the flow type in the cavity to change from open to closed. The increase of the Mach number inhibits the shear layer from expanding into the cavity and induces the main recirculation vortex to move back and the flow type to be open. The amplitude of the overall sound pressure level is positively correlated with the flow velocity in the back of the cavity.
Calibration results and analysis of thin-film gauges calibrated with the transfer method
YANG Kai , LIU Jichun etc.
 doi: 10.11729/syltlx20210129
[Abstract](105) [FullText HTML](12) [PDF 6370KB](1)
Considering the fact that there are more error sources in the measured heat flux with thin-film gauges when the two-stage approach is applied to determine the thermal product and resistance-temperature factor, the transfer method is applied to directly calibrate thin-film gauges, in which the thermal product and resistance-temperature factor are treated as the sensitivity coefficients. To get the consistent calibration results of different thin-film gauges fabricated in a batch, the sensitivity coefficients are divided by the resistance-temperature factors of the thin-film gauges, and then the correction sensitivity coefficients are consistent. With the transfer calibration technique, the calibration results of thin-film gauges show a good linearity with a relative expanded uncertainty below 6.5%, which is lower than that reported in other researches, in which the two-stage approach is used to calibrate thin-film gauges.
Experimental study on Rayleigh–Bénard convection during supercritical phase transition of carbon dioxide
ZHAO Yifan , WU Di etc.
 doi: 10.11729/syltlx20230003
[Abstract](11) [FullText HTML](2) [PDF 10764KB](0)
Supercritical fluid is a kind of special fluid under extreme conditions (temperature and pressure are above the critical point). The Rayleigh-Benard (RB) convection of supercritical fluid driven by buoyancy is a new nonlinear thermal convection system. Its buoyancy does not conform to the Boussinesq approximation. Under the action of temperature difference, the physical properties of RB fluid show severe distortion near the critical point, accompanied by abundant flow and phase transition coupling processes. In this experiment, a transparent sapphire pressure vessel capable of carrying supercritical carbon dioxide (SCO2) was designed to establish RB convection of supercritical fluid under the effect of vertical temperature gradient. The flow structure and supercritical phase transition process under different temperature differences were observed. The velocity field of "atomized" droplets was calculated by image cross-correlation algorithm. In the experiment, platinum resistance temperature measurement was used to accurately control the temperature of the upper and lower ends of the container, and the evolution of various flow modes and velocity fields in the linear cooling process was studied. In the linear cooling process, SCO2 goes through three typical processes: supercritical flow, transcritical flow and gas liquid two-phase flow. The strong coupling of the transcritical phase transition with buoyancy convection results in the heterogeneous unsteady flow of supercritical carbon dioxide RB convection. It shows that the supercritical RB convection is extremely sensitive to temperature difference, and the larger the temperature difference is, the more intense the convection in the supercritical domain is. With the decrease of temperature, the atomized droplets condense to form abundant structure of multi-layer flows, which finally turn to the two-phase flow.
Measurement investigation of rotational temperature and vibrational temperature in hypersonic wind tunnel rarefied flow field
CHEN Aiguo , TIAN Ying etc.
 doi: 10.11729/syltlx20210192
[Abstract](7) [FullText HTML](2) [PDF 7297KB](1)
The inconsistency of rotational temperature and vibrational temperature in the rarefied flow field is a concrete manifestation of thermodynamic non-equilibrium. The non-intrusive measurement method of rotational temperature and vibrational temperature in the rarefied flow field can be measured by the Electron Beam Fluorescence (EBF) technique. The basic principle and measurement method of EBF were introduced in this paper. Experiment was carried out in the M12 and M16 conical nozzle of the Φ0.3m hypersonic low density wind tunnel. The rotational temperature maximum relative uncertainty is 0.26% and the vibrational temperature maximum relative uncertainty is 0.8% from the analysis of repetitive measurement results. The distribution of rotational temperature and vibrational temperature on the exit section of the M12 and M16 conical nozzle reflects the characteristics of expansion flow of the conical nozzle. The measurement results of three states of each nozzle show that with the increase of rareness, the larger the deviation between the vibrational temperature and the rotational temperature is, the more prominent the thermodynamic non-equilibrium phenomenon appears.
Research progress of improving nanofluid fuel performance
GAO Yi , XU Xingxing etc.
 doi: 10.11729/syltlx20220119
[Abstract](19) [FullText HTML](11) [PDF 7312KB](3)
Nanofluid fuel is a kind of suspension liquid, which is made by adding nanoparticles into the liquid fuel. It has advantages of high energy density and shorter ignition delay, and thus shows the potential of improving the burning characteristics of the fuels. To further improve the performance of nanofluid fuels and explore more effective performance control methods, the progress of research on nanofluid fuels in recent years at home and abroad is briefly reviewed in this work. Researches on the improvement of the stability performance, rheological performance, evaporation performance, ignition performance and combustion performance of nanofluid fuels are introduced, and the corresponding tailoring methods and mechanisms are analyzed. Adding surfactant and surface coating are effective methods to improve the stability of nanoparticles in the fuel. The methods of regulating ignition and combustion performance are based on improving the heat conduction and absorption capacity of droplets and promoting the heat release of metal particles, which mainly include nano-metal particles, nano-metal oxides, and new metastable intermixed composites. The existing problems in current research are summarized. More importantly, it is pointed out that the future study of nanofluid fuels should focus on broadening the boundary of the fuel, exploring new surfactants, and establishing the theoretical framework of ignition and combustion.
Progress on fluid-solid coupling of vacuum pipeline train and analysis of key technology
KOU Jie , FU Cheng etc.
 doi: 10.11729/syltlx20220143
[Abstract](53) [FullText HTML](22) [PDF 6940KB](6)
Theoretically, the speed of vacuum pipe trains can exceed 1000 km/h by using the magnetic suspended technology in a low-pressure operating environment of pumped vacuums within the tubes. The closed pipe creates a complex aerodynamic environment, while the suspension of the train makes it very susceptible to changes in the attitude of the train. The fluid-solid coupling effects of the train are evident which require targeted research. In order to explore the theory and analysis method of fluid-solid coupling of the vacuum pipeline train, a relatively complete review of the progress in aerodynamic studies of the vacuum pipe train and the study of the fluid-solid coupling characteristics of the railway trains is made. And the key technology of fluid-solid coupling of the vacuum pipeline train is analyzed. It is proposed that the vacuum pipe train fluid-solid coupling study should focus on the development of the vacuum pipe train flow analysis techniques, the vacuum pipe train fluid-solid coupling analysis techniques and the vacuum pipe train control technology. This paper provides reference for vacuum pipe train fluid-solid coupling techniques to facilitate the development of the vacuum pipe train technology.
Multi-objective optimization method for light-field multi-spectral pyrometer
SUN Linlin , FANG Hua etc.
 doi: 10.11729/syltlx20230011
[Abstract](45) [FullText HTML](13) [PDF 5429KB](8)
A light-field multi-spectral pyrometer is designed for two-dimensional, high-temperature measurements. The proposed method is based on an unfocused light-field camera, which can simultaneously record directions and intensities of incident rays. The direction information of rays is substituted by radiation spectrums via placing an array of filters in front of the camera’s main lens, such that the image sensor can simultaneously acquire spectra and intensities of rays. For multi-spectral data processing, how to obtain the accurate target temperature under unknown spectral emissivity is a difficult problem to be solved. A multi-objective optimization method is proposed to obtain the inverse true temperature and spectral emissivity without assuming the emissivity model. In this method, the multi-objective function is established according to the radiation equations. The emissivity constraint conditions are set for the objective function, and the penalty function method is used to solve the optimization problem. The calibration experiment results of the black-body furnace show that the relative error of the light-field multi-spectral pyrometer method is less than 1%, which proves the feasibility and reliability of the proposed design and temperature inversion method.
The effect of track structure on the aerodynamic characteristics of evacuated tube maglev train
WANG Xiaofei , HU Xiao etc.
 doi: 10.11729/syltlx20220140
[Abstract](48) [FullText HTML](19) [PDF 14083KB](10)
The emergence of evacuated tube maglev transportation makes it possible for ground ultra-high-speed rail transit. However, limited by the demand for high-power propulsion motors and low vacuum environment, it is difficult to carry out experimental research. In this paper, the numerical research on the aerodynamic layout of the magnetic track and motor is carried out in the preliminary design of the Dynamic Model Test Platform for Multistate Coupled Rail Transit. Based on the geometric structure of the dynamic model test platform, considering the actual arrangement of the motor platform and the permanent magnet track in the tube, the three-dimensional, compressible RANS method and SST k–ω turbulence model are used to calculate the three-dimensional flow field structure and the shock wave reflection, propagation law of the superconducting maglev train in the low-pressure tube at ultra-high speed. The influence of the rectangular channel on the aerodynamic loads of the train and the flow field in the tube is compared and analyzed. The differences of the pressure and velocity change trend at the bottom of the train, and the shock wave strength at the tail and the wake structure are mainly explored. It is found that the step of the magnetic track and the motor can cause more flow separation and shock reflection in the wake region, resulting in tail pressure fluctuations. When the rectangular channel exists, the shock wave intensity at the tail of the train decreases, the shock wave phenomenon is more obvious, the aerodynamic drag coefficient decreases by 8.855%, and the aerodynamic lift coefficient increases by 14.312%. The research results can provide reference for the design of the magnetic track and motor platform of the multi-state coupling rail transit dynamic model test platform.
Two-dimensional distribution measurement of direct-connect scramjet combustion flow field based on TDLAS multi-absorption lines
XIA Huihui , ZHANG Shunping etc.
 doi: 10.11729/syltlx20220103
[Abstract](33) [FullText HTML](16) [PDF 6180KB](5)
Aiming at the demand of two-dimensional distribution high-resolution measurement of temperature and water vapor concentration in non-uniform scramjet combustion chamber expansion section, advanced tunable diode laser absorption spectroscopy (TDLAS) reconstruction method has been developed. By increasing the number of water vapor absorption lines obtained by scanning the laser wavelength, the number of equations for solving the reconstruction problem correspondingly increased, combining the absorbance equations of all absorption spectra under all laser paths, constructing the optimization objective function with temperature and concentration as unknowns, and using the global optimization simulated annealing algorithm to reconstruct the temperature and water vapor concentration distribution. In the direct-connect scramjet combustion test, the orthogonal optical path layout is adopted, and the square optical mechanical structure with 16 measuring optical paths of 5 horizontal and 11 vertical channels is designed. TDLAS measurement system is assembled, and the time division multiplexed direct absorption detection method is adopted for 5 DFB lasers, with the measurement frequency of 4 kHz. Five water vapor absorption spectral lines (7467.77、7444.36、7185.60、7179.75 and 6807.83 cm) can be obtained at each measured optical path, the system has carried out thermometric validation by using high-temperature furnace on the laboratory, and the temperature measurement deviation is within 2.7%. In the test, the absorption spectrum data synchronously collected under 16 optical paths are processed offline, and the distribution data of temperature field and water vapor partial pressure under various states of ignition, combustion and flameout are obtained. The test results show that TDLAS multi-absorption measurement technology can realize accurate and stable reconstruction, and meet the engineering application requirements of complex combustion flow field diagnosis and bad working conditions.
Experimental study on flow characteristics of pitching hydrofoil via stereo shadowgraph
WEI Jinwu , MEI Xiaohan etc.
 doi: 10.11729/syltlx20220095
[Abstract](53) [FullText HTML](23) [PDF 8306KB](4)
In order to study the jet flow characteristics caused by the pitching hydrofoil, a three-dimensional shadow imaging system is utilized to measure the turbulent flow field. By comparing the results of particle image velocimetry, two-dimensional particle tracking velocimetry and three-dimensional particle tracking velocimetry, it is found that the pure pitch motion of the rigid symmetric NACA0012 airfoil at a fixed position in the static fluid would produce weak jets in two directions, accompanied by the generation of small-scale vortices. The results of velocity statistics show that when the amplitude of the hydrofoil rational angle is large, more obvious vortex structure and velocity change are produced. The study obtained the three-dimensional wake structure generated by the pitching hydrofoil movement, and found that there is also a symmetric vortex structure in the depth direction. The results show that the velocity component in the depth direction generated by the pitching hydrofoil movement can not be ignored under the limited airfoil aspect ratio.
Application of typical magnetic suspension system in maglev flight wind tunnel
YU Xinning , JIANG Xintong etc.
 doi: 10.11729/syltlx20220149
[Abstract](76) [FullText HTML](11) [PDF 6477KB](11)
The operation principle of the maglev flight wind tunnel is to drive the model to move at high speed in a closed straight pipe through magnetic suspension. The maglev system is particularly important for accurate control of the acceleration/uniform/deceleration process of the model. This study made a comprehensive analysis of the four maglev systems, including normal conductive electromagnetic suspension (EMS), permanent magnet electrodynamic suspension (PM–EDS), high/low temperature superconducting electrodynamics suspension (HTS/LTS–EDS), and high temperature superconducting pinning levitation (HTS–PL). These several maglev systems were comprehensively analyzed from five aspects. EMS system could not meet the specification requirement of the maximum operating speed Ma=1.0, which could not be used as an alternative maglev system for the maglev flight wind tunnel. Based on the analytic hierarchy process (AHP) and grey relational analysis (GRA), a comprehensive decision-making model of the maglev system was established for the application scenario of the maglev flight wind tunnel. Results show that the HTS–EDS and HTS–PL system have better application potential in the maglev flight wind tunnel.
Study on electric and thermal characteristics of CO2 arc heater
OU Dongbin , YANG Guoming etc.
 doi: 10.11729/syltlx20220065
[Abstract](35) [FullText HTML](25) [PDF 7131KB](4)
On the 300 kW DC axial tube electrode arc heater, the UI characteristics and thermal efficiency of CO2 and air are measured by experiment, and the regression analysis is carried out by using the similarity criterion number. The unified relationship of electric and thermal characteristics that can be applied to the two media is obtained, and compared with similar heaters abroad. The results show that CO2 and air arc heaters have similar electric and thermal characteristics, under the same input parameters (arc current and gas flow); the total pressure of CO2 is 18% lower than that of air, but the arc voltage, enthalpy and thermal efficiency are 5.9%, 6.7% and 10.9% higher respectively; the regression errors of UI characteristics and thermal efficiency are −13.0%~11.4% and −33.0%~34.7% respectively. This relationship plays an important guiding role in the operation and commissioning of the high-power arc heater.
Influence and regulation of magnetic field on wettability of ferrofluid droplet on hydrophobic surface
OUYANG Yi , WEN Mingfu etc.
 doi: 10.11729/syltlx20220086
[Abstract](73) [FullText HTML](26) [PDF 7437KB](15)
The controllable dynamic behavior of ferrofluid droplets under the magnetic field can be used to realize directional transport of small droplets or bubbles in microfluidic devices, anti-icing, droplet condensation, mineral flotation and other fields. At present, the mechanism, influencing factors and regulation methods of the field-assisted wetting behavior of magnetic fluid on the superhydrophobic surface are not clear. The wetting behavior and droplet shape evolutions of water-based ferrofluid on a hydrophobic surface under an external magnetic field are studied experimentally. Under the vertical magnetic field, the effects of the magnetic induction intensity and ferrofluid droplet size on the droplet wetting behaviors are investigated, and the contact line diameter and contact angle of the droplet are measured experimentally. The experimental results show that the apparent contact angle of the ferrofluid droplets decreases from above 90° to below 90° under the action of the weak magnetic field. Under the magnetic field, the nanomagnetic particles in the magnetic fluid form a chain structure along the direction of the magnetic field line and the droplet contact angle changes. Through a scaling analysis, the theoretical relationship of the magnetic field and the contact angle is established and it successfully predicts our experimental results. The work is valuable for controlling the wetting properties of the ferrofluid droplets on the solid surfaces under the magnetic field.
A brief review on trans/supercritical internal flow and jet
JIANG Guanyu , WEN Haocheng etc.
 doi: 10.11729/syltlx20220083
[Abstract](82) [FullText HTML](40) [PDF 7495KB](7)
Aviation kerosene is expected to act as the primary coolant of advanced gas turbine engines. In such situations, the aviation kerosene would exist at subcritical conditions near the critical point or even at supercritical conditions. Correspondingly, it is of vital importance to study the nozzle internal flow and jet for the design of engine combustors. This paper focuses on the internal flow characteristics and jet characteristics under trans/supercritical conditions. The review shows that the existing researches of the trans/supercritical internal flow are mainly limited to small-molecular or simple fluids, constant cross-section pipes, and narrow conditional parameters. The location of phase change depends on thermodynamic characteristics, geometric configurations, and injection parameters. The mixing efficiency of the trans/supercritical jet is largely affected by thermodynamic characteristics. However, the research on trans/supercritical internal flow characteristics of hydrocarbon fuel inside constriction nozzle channels and jet characteristics based on relatively complex nozzle configurations remains to be further developed. Accurate thermodynamic models of supercritical aviation kerosene remain to be established. The deformation and breaking mechanism of the jet fluid interface as well as the jet mixing behavior remains to be captured through advanced optical diagnostic methods. The mixing characteristic parameters and their change laws remain to be summarized and described.
1.2 m large-field focusing schlieren technique
XIE Aimin , XING Yanchang etc.
 doi: 10.11729/syltlx20220047
[Abstract](81) [FullText HTML](33) [PDF 7524KB](14)
In the conventional “Z” structure schlieren technique, due to the limitation of large-size optical element materials and processing technology, the size of the test field is usually less than 1 meter. In order to show the flow field of a large-scale model in a wind tunnel, the focusing schlieren technique is proposed to show the flow field in the 1.2 m test area. According to the imaging principle, the large size Fresnel lens are replaced by a matrix light source. After solving the key technologies such as the engineering design of large-size light source splicing, the development of large-diameter focusing lens and the production of high-definition imaging screen, two sets of focusing schlieren systems with the test field of view of 1.2 m × 1.2 m were established, and the schlieren images of the hypervelocity flow field with high sensitivity were obtained in the wind tunnel. The flow visualization with larger field is expected to be realized through the splicing of larger size light sources.
Research on flow characteristics of underwater passive fluidic thrust vectoring nozzle
FENG Chao , GU Yunsong etc.
 doi: 10.11729/syltlx20220071
[Abstract](60) [FullText HTML](32) [PDF 10196KB](6)
We designed an underwater passive fluidic thrust vectoring nozzle. It can easily generate pressure difference on both sides of the primary jet to deflect the jet only by controlling the valves of the secondary flow channel. However, the nonlinear features in the control law of the thrust vectoring angle such as “sudden jump” and “hysteresis” limit the further application of this technology. In this research, the flow characteristics of the primary jet in different transverse sections of the nozzle were studied by the dye flow visualization technology and particle image velocimetry technology. We discovered flow structures such as shear layer vortices, trailing edge backflow, and separation bubbles. Three-dimensional flow structures were also observed, including the transverse flow in the near-wall region and the corner flow at the joint of two walls. The study of the interaction law between flow structures provides a physical model basis for solving the nonlinear problems such as jump and hysteresis of the thrust vectoring control law.
Roll-yaw control of flying wing aircraft at a high angle of attack based on jet control
GE Zengran , SHI Zhiwei etc.
 doi: 10.11729/syltlx20220104
[Abstract](71) [FullText HTML](26) [PDF 7105KB](12)
The complex flow field structure and the interaction between vortex structures make the flying wing configuration aircraft prone to transverse uncommanded motion at a high angle of attack. To suppress the uncommanded motion, two sets of jet actuators are arranged on the vehicle using two existing active jet control techniques, the control effect of the actuators is verified through wind tunnel force measurement experiments, and the mutual coupling relationship between the two sets of jet actuators is clarified. A virtual flight experiment is conducted in the wind tunnel to capture the uncommanded motion of the flying wing configuration aircraft in the transverse direction, and two methods, PID and deep reinforcement learning, are applied to suppress the uncommanded motion in this kind of highly coupled and nonlinear problem. The wind tunnel experiments show that the deep reinforcement learning method is more effective in controlling the highly coupled and nonlinear problem, and the trained intelligent model can effectively suppress the transverse uncommanded motion of the flying wing configuration aircraft model.
Experimental study on characteristic calibration of separated exhaust system
LI Qiufeng , LI Mi etc.
 doi: 10.11729/syltlx20220056
[Abstract](43) [FullText HTML](24) [PDF 8779KB](2)
In flight testing, the aeroengine flight thrust is indirectly obtained by the gas generator method. In order to improve the calculation accuracy of the flight thrust, it is necessary to accurately obtain the characteristics of the exhaust system. The laboratory calibration test and numerical simulation research were carried out by using the large bypass ratio separated exhaust system scale model. The results show that: the core nozzle characteristics obtained by the two methods are consistent, and the values are close. When the maximum core nozzle pressure ratio is 1.44, the deviations of the mass flow and the thrust are 0.73% and 0.18%, respectively; the characteristics of the separated exhaust system obtained by the two methods have the same trend and close values. When the max bypass nozzle pressure ratio equals 1.46, the deviations of the mass flow and the thrust are 0.64% and 0.18%, respectively; when the physical model and geometric model of the large bypass ratio separated exhaust system are reasonably simplified, the characteristic deviations of the separated exhaust system obtained by the two methods are in good agreement.
Research on the double-inlet test method in low speed wind tunnel
TANG Jianping , SHANG Yinhui etc.
 doi: 10.11729/syltlx20220059
[Abstract](63) [FullText HTML](28) [PDF 13166KB](5)
In order to meet the requirement of the double-inlet test in the 4 m magnitude low speed wind tunnel, a test method of the double-inlet test in the 4 m × 3 m low speed wind tunnel of LSAI of CARDC was proposed. According to the method, a model is supported by one pole, and each inlet mass flow is simulated and controlled by an ejector with a digital pressure regulating valves system. In this method, the range of AOA is −10°~90°, the range of AOS is −45°~45°, the simulating maximum of the double-inlet mass flow is 2.9 kg/s and 1.4 kg/s. To validate the method, a double-inlet test was completed in the low speed wind tunnel. The test results show: the model is less affected by pipeline aerodynamics. The independent model and ejector support mechanism meets various model support requirements. Double inlets mass flow simulation and control are completely independent, which meets the requirement of studying interactions for double inlets.
Experimental investigation on anti-icing mechanism and characteristics of superhydrophobic electrothermal coupled surface
LIU Xinle , LI Wenfeng etc.
 doi: 10.11729/syltlx20220062
[Abstract](101) [FullText HTML](56) [PDF 9559KB](8)
As a novel anti-icing technology, superhydrophobic electrothermal coupled surface anti-icing possesses an excel-lent anti-icing efficiency with low energy consumption. Based on the water droplet impact behaviors and the wetting characteristics of the superhydrophobic surface, a prediction model of the heat flow density of superhydrophobic electrothermal coupled surface anti-icing is developed according to the thermal balance theory of the icing surface. The experimental analysis of the superhydrophobic electrothermal coupled surface anti-icing is carried out in a low-speed icing wind tunnel. The results show that the difference between the theoretical anti-icing heat flux and the experimental results is less than 6%, which verifies the prediction model. The analysis of the experimental results and energy consumption shows that the superhydrophobic electrothermal coupled surface anti-icing effectively reduces the energy consumption compared with the electrothermal method. With the freestream velocity of 10 m/s, liquid water content of 1 g/m3, mean volume diameter of 65 μm, and temperature of −15 ℃, the superhydrophobic coating can effectively prevent the formation of backwater due to its wetting property. For dry and wet surface anti-icing, the superhydrophobic electrothermal coupled surface anti-icing method reduces the energy consumption by about 43% and 33% respectively compared with the electrothermal method.
PLIF investigation on effects of chamber aspect ratio on flow and mixing in cross-shaped mixers
YANG Huan , ZHANG Wei etc.
 doi: 10.11729/syltlx20220038
[Abstract](55) [FullText HTML](10) [PDF 7176KB](9)
Planar Laser-induced Fluorescence (PLIF) was used to study flow and mixing characteristics in cross-shaped mixers with four chamber aspect ratios rr=0.5, 1.0, 1.5 and 2.0) at 10<Re<500. Results show that, there are four flow regimes in the mixers with different depths, including the segregated flow, steady engulfment flow, pulsation flow and unsteady engulfment flow. For the steady engulfment flow, the flow field is dominated by three co-rotating vortices for r<1.0, but the center and satellite vortices rotate in opposite directions for r≥1.0. For the pulsation flow, the center vortex shrinks and expands periodically, and the fluid oscillates throughout the chamber for r>1.0. For r=1.0 and 0.5, the shedding of vortex rings emerges downstream. For the unsteady engulfment flow, periodical vortex merging and breakup is observed for r=1.0. For r=0.5, vortex breakup is invisible, and instead, the center vortex merges with a satellite vortex periodically. For r>1.0, the center vortex experiences growth, deformation, and breakup processes. Mixing in cross-shaped mixers was evaluated by the time-averaged intensity of segregation (IOS), and the mixing mechanism is revealed. An increase in chamber aspect ratios decreases the critical Reynolds number for the engulfment flow and pulsation flow, which causes the mixing enhancement in the chamber at low Re.
Ice cloud parameter identification method in icing wind tunnel based on multimodal fusion
XIE Teng , XIONG Hao etc.
 doi: 10.11729/syltlx20220077
[Abstract](79) [FullText HTML](48) [PDF 7957KB](12)
The cloud field calibration of icing wind tunnels usually has the disadvantage of high instrument dependence. To solve this problem, this paper proposes a method for identifying the parameters of cloud fields in icing wind tunnels based on multi-modal fusion. This method takes the icing image of the test model together with the parameters such as the angle of attack, air velocity, air temperature, and icing duration of the model as input, extracts and fuses the two characteristic parameters, and takes the liquid water content (LWC) and the average volume diameter of water droplets (MVD) as the output to train the neural network model. And then the rapid identification of icing cloud parameters is realized. In order to verify the effectiveness and feasibility of the proposed method, the paper takes NACA0012 airfoil icing as the research object, develops the cloud field identification program of the icing wind tunnel, analyzes the influence of the fusion proportion, and obtains the best network model suitable for ice parameter identification. On this basis, simulation and experimental evaluation are carried out. The full scale error of the proposed method for LWC and MVD is less than 12%, which has high identification accuracy and good generalization performance, and can provide an important supplement for the identification of cloud fields in the icing wind tunnel.
Experiment of aerodynamic performance of axial compressor at low Reynolds number condition
LEI Pengfei , ZHOU Enmin etc.
 doi: 10.11729/syltlx20220026
[Abstract](85) [FullText HTML](36) [PDF 6746KB](8)
Aerodynamic performances of the axial compressor of the 0.6 m continuous transonic wind tunnel are tested under various pressure conditions, and the Reynolds number effects are studied experimentally. The lowest total pressure of the compressor inlet is about 3 kPa, and the corresponding Reynolds number is approximately 5×104. Test results show that the Reynolds number effects are significant when as Reynolds number is below the critical value, which is 5×105 in the compressor design. Compared to the large Reynolds number condition, the pressure ratio under the low Reynolds number condition reduces rapidly, while the surge margin changes slightly. The mechanical loss of the shaft becomes the major loss of the compressor as the operation pressure drops, and has a significant influence on the compressor efficiency. Additionally, the correlations of the pressure ratio and efficiency with Reynolds number, obtained by data analysis, can offer a useful reference for design and numerical simulation of the axial compressor under the at low Reynolds number condition.
Crossing shock waves/transitional boundary layers interactions in the double vertical wedges configuration
YI Miaorong , ZHANG Ruoling etc.
 doi: 10.11729/syltlx20220050
[Abstract](94) [FullText HTML](43) [PDF 7850KB](10)
Study on crossing shock waves/transitional boundary layer interaction in the double vertical wedges configuration was carried out using wind tunnel tests and numerical calculations. The wind tunnel tests were carried out at Φ 600 mm pulse combustion wind tunnel. The Mach number of the free stream condition is 3.0, and the unit Reynolds number is 2.1×106 m−1. The schlieren images, wall pressure and wall heat fluxes were obtained during the tests. The results show that because of the adverse pressure gradient caused by the crossing shock waves, the separation of the laminar boundary layer was captured near the shock waves intersection point. And the transition from laminar to turbulent occurred rapidly in the interaction region. After installation of vertex generator devices or roughness devices, the boundary layer transition position moved to the upstream of the interaction region, the separation was effectively inhibited. And the heat fluxes in the interaction region declined obviously. The peak value of heat fluxe was reduced by more than 25%. The shock wave structures and wall pressure distributions obtained from tests and simulations agreed well, while the prediction heat fluxes were much larger than the test results. The comparison between the calculated results of the transition model and the turbulence model shows that the obviously larger turbulence viscosity is the main reason why RANS methods over-predict the heat fluxes in the unseparated interaction region.
Improvement, performance test and evaluation for Schmidt–Boelter gage
ZHU Tao , YANG Kai etc.
 doi: 10.11729/syltlx20220029
[Abstract](159) [FullText HTML](70) [PDF 6712KB](21)
A kind of the small size Schmidt–Boelter gage was improved for measuring dynamic heat flux in the continuous variable attack angle test in the conventional hypersonic wind tunnel. The Schmidt–Boelter gage improved was statically calibrated and dynamically tested by the heat flux calibration devices. The test results show that the sensitivity coefficient is 57.67 μV·kW−1·m2, the response time is 27 ms, the cut-off frequency is 26 Hz and the gage range coverage is 1–130 kW/m2. Then the quantitative relation between the continuous variable attack angle velocity and the maximum test error was established based on the feature response time constant. And referring to the heat flux measured in the step variable attack angle test, the maximum velocity of the continuous variable attack angle supported by the gage was evaluated within a certain margin of error.
Mechanism study of free-surface polygons formation in rotating fluids
LI Weiyi , WANG Tao etc.
 doi: 10.11729/syltlx20220074
[Abstract](64) [FullText HTML](24) [PDF 7871KB](8)
In order to study the formation mechanism of polygon phenomenon in rotating fluid, a test set-up of rotating cylinder which can produce rotating fluid was designed. Experiments on rotating fluid for different rotational frequency, liquid heights and radiuses of cylinder were performed. Based on experimental results, a composite wave theoretical model of the intersection point between the free surface of fluid and the bottom of the container was established according to the wave equation and ignoring the specific movement inside the fluid. On this basis, the theoretical model was verified by experiments, and the rotation state on the experimental phenomenon was further studied. Based on the experimental data and previous work, this paper made empirical formula fitting to the data, and found that the fitting effect of blackbody radiation model is the best. The main conclusions are shown below: 1)The viscous action caused by the relative motion between the rotating fluid and the wall causes the free surface of the fluid to form a polygon, which is related to the rotation frequency, the radius of the container, the height of the liquid surface, and the density and viscosity of the fluid, which can be shown by the phase change of the wave. 2)The radial motion of the intersection point between the free surface of the fluid and the bottom of the container can be regarded as the result of the interaction between the gravity pressure field, the centrifugal field and the reflected wave of the vessel wall and the viscous force of the vessel wall, and the radial wave equation can be approximately described by simple harmonic motion. after the parameters of the wave equation satisfy certain constraints, the free surface profile can be obtained by near Fourier transform projection. 3)For a single influence factor, the number of polygonal edges on the free surface of the rotating fluid is positively related to the rotation frequency and negatively related to the height of the liquid surface. The larger the radius of the cylinder is, the easier it is to form polygons. 4)For more influencing factors, the angle number of polygons on the free surface of rotating fluid is mainly related to the two dimensionless quantities of R/H and 1/Ek. With the increase of 1/Ek, the number of angles increases, but the range of adjacent transition boundaries decreases gradually. In the experiment, the more the number of corners, the more unstable the polygon. The disturbance caused by a slight change in rotation frequency will change the number of angles. In the experiment, there is a R/H value in the range of [2.4, 2.5], which makes polygons form most easily, and the 1/Ek range of adjacent transition boundaries is also the largest. 5)When R/H∈[2.0, 4.0], the relationship between the angle number of the rotating fluid and 1/Ek accords with the blackbody radiation model curve, which indicates that the hypothesis of the fluid complex wave may be related to the harmonic oscillator hypothesis of the blackbody radiation. When R/H>4, the constraint effect of the wall is weakened, and the blackbody radiation model can only be used for qualitative prediction. The phenomenon is explored from the theoretical point of view, and the empirical formula is fitted from the experimental point of view. The results can be further applied to theoretical research to determine the physical mechanism of the phenomenon.
Research on the dynamic derivatives test technology of 4.5 m × 3.5 m low speed wind tunnel
CHEN Hao , BU Chen etc.
 doi: 10.11729/syltlx20210131
[Abstract](96) [FullText HTML](47) [PDF 7519KB](9)
The dynamic derivatives are the a necessary parameters in the process of analyzing the stability of the aircraft and designing the control law, in order to meet the demand for obtaining high-precision dynamic derivatives data for large-scale aircraft. Aerodynamics Research Institute of Aviation Industry Corporation of China (AVIC) developed a dynamic derivatives test system with five kinds of oscillations in the 4.5 m × 3.5 m low-speed wind tunnel. The test system uses servo hydraulic swing motor and servo hydraulic cylinder as the driving components of the motion, and directly generates arbitrary waveform motion with the control of the servo valve. The driving mode of the system has the characteristics of small movement transmission gap, high movement control precision, and high automation. The scale of the test model is up to 2.5 m, with the wind speed v =30~60 m/s, the angle of attack α= −36°~36°, and the sideslip angle β= −40°~40°. The verification tests of the dynamic standard model and a wing-body model were carried out, and the test results show that the dynamic derivatives data obtained by the test system is reasonable, the accuracy of the repeatability test data is within 3%, and the test system can provide high-quality dynamic derivatives data for large-scale aircraft.
Research on the position control of double-pass schlieren component based on visual feedback
FANG Bihong , LI Ming etc.
 doi: 10.11729/syltlx20220068
[Abstract](60) [FullText HTML](36) [PDF 8409KB](5)
The traditional mechanical method of debugging the double-pass schlieren system exhibits the problems that the fine positioning of the working position of the spherical mirror mechanism cannot be ensured, and the optical paths cannot be completely coincided after passing through the flow field twice in the experimental application in the hypersonic low density wind tunnel. Here, a novel double-pass schlieren system based on visual feedback was developed. The system via absolute encoder instruction control the AC servo motor to adjust the position of the spherical mirror mechanism. Moreover, the pitch and left-right deflection of the spherical mirror can be adjusted by the schlieren image quality evaluation results provided by the machine vision system(visual information feedback). The position control system of double-pass schlieren parts based on visual feedback realizes the automatic positioning closed-loop control of the double-pass schlieren spherical mirror mechanism, and ensures that the light paths overlap as much as possible after passing through the flow field twice to eliminate ghosting during imaging of the model flow field(the definition of the flow field image is improved by 2.2 times compared with that obtained by the traditional method).
Research of the continuous scan test method for inlet in low wind tunnel
XU Binbin , LIU Tingshen etc.
 doi: 10.11729/syltlx20220032
[Abstract](68) [FullText HTML](54) [PDF 6901KB](11)
The continuous scan test method for the inlet of airplane was studied in the FL–13 wind tunnel of CARDC. The test methods and procedures were proposed and the test data processing methods were also provided. Inlet tests were performed in the FL–13 wind tunnel to compare the conventional test method with the continuous scan test method. The test results with the continuous scan test method have a good consistency with the conventional test method, which verifies the availability and feasibility of the continuous scan test method for the inlet in the low speed wind tunnel. The research results show that the continuous scan test method can raise the tests efficiency and acquire more test data for the inlet test in the wind tunnel.
Optimization of total enthalpy measurement method based on the total temperature probe
ZHU Xinxin , LONG Yongsheng etc.
 doi: 10.11729/syltlx20210149
[Abstract](113) [FullText HTML](33) [PDF 6978KB](14)
A kind of total temperature probe with Iridium Rhodium Iridium thermocouple is developed for improving the total enthalpy measurement accuracy. The size parameters of each component are optimized based on the fluid-thermal coupling model of the probe. The reheating rate of the probe is not less than 0.9 after optimization. The calculation and test results show that the temperature of the thermocouple node rises slowly as the temperature of the thermocouple tail and the shielding case rises. This fact results in the temperature of thermocouple node changing according to the measurement time period. So the measurement time period of the total temperature value should be regulated and the total temperature value must be calibrated. Therefore, a comparison calibration method is proposed, in which the total temperature probe used in the supersonic flow field can be traced to the standard calibration device in the subsonic flow field by an arc chamber total probe developed. Finally, the total enthalpy measurement test based on the total temperature probe is carried out in the arc heated wind tunnel. And the uncertainty of the total enthalpy measurement is calculated according to the uncertainty evaluation method based on the precision limit and deviation limit. The test results show that the total temperature probe has a high total enthalpy measurement accuracy. The repeatability precision is about 3% and the uncertainty is 6.4% in this test.
Study on interaction between wing tip vortex and flat tail tip vortex
ZHANG Zeyu , LI Dong etc.
 doi: 10.11729/syltlx20210116
[Abstract](81) [FullText HTML](41) [PDF 9730KB](11)
The development of the wingtip vortex is an important factor for the flight safety and airport efficiency of the aircraft landing on the runway. The near-field characteristics of the wingtip vortex mainly determine the vorticity of the vortex in the landing phase. In this paper, a simplified model of A320 is used as the object to observe the near-field configuration of the wingtip vortex in a low-speed tunnel of 1 m × 1 m. It is found that the horizontal tail vortex rotates around the wingtip vortex, and the rotational angular velocity in different flow stations is different. By comparing the simulation results, it is found that the rotational angular velocity of the horizontal tail vortex around the wingtip vortex is basically consistent with the experimental results, indicating that the development of the wake vortex under different Reynolds numbers has certain similarity in the characteristics of the rotational angular velocity between two vortices.
Flash infrared thermal wave detection of Ice surface edge
GOU Yi , LI Qingying etc.
 doi: 10.11729/syltlx20220017
[Abstract](118) [FullText HTML](76) [PDF 7607KB](7)
Ice accretion detection is an important means to ensure flight safety and an important issue in the field of aircraft anti-icing. In this paper, the method of identifying the boundary between the ice surface and the interior is discussed by using the infrared thermal wave detection technology. With a flash infrared thermal wave detection system established, regular ice accretion samples and ice accretion samples with internal boundary were made, the ice accretion detection experiments were carried out, and the data of the infrared thermal wave sequence were collected. In addition, the traditional algorithm based on the first-order differential operator and the second-order differential operator was exploited for processing the ice edge. A new boundary recognition method was proposed as well, which combined the gauss-Pierre-Simon Laplace pyramid algorithm and the area filtering algorithm. Then, the feasibility of the proposed algorithm to identify the boundary of the ice accretion surface was discussed and compared. The experiments and the image data processing methods show that the traditional algorithm can successfully recognize the outer boundary of ice accretion, but can not accurately recognize the internal boundary of ice accretion. The new fusion algorithm can effectively recognize the ice edge and the internal boundary, but the image noise is higher than that of the traditional algorithm. It can be concluded that the new fusion algorithm has some advantages in the detection of the irregular icing surface, and it is expected to provide a new research idea for icing detection in the field of aircraft anti-icing.
Wind tunnel force test of fairing separation in hypersonic and high dynamic pressure situation
ZHONG Jun , LIN Jingzhou etc.
 doi: 10.11729/syltlx20210194
[Abstract](240) [FullText HTML](111) [PDF 9052KB](23)
For the problem of the monolithic fairing separating from a hypersonic test demonstrator in a high dynamic situation, the reverse-thrust jets simulation method and wind tunnel force test model design have been developed, to meet the requirements of simulating the jets interaction effect and separation distance influence in the hypersonic wind tunnel. The fairing’s aerodynamic characteristics, including the jets interaction effect and the separation distance influence, were obtained by the strain balance in circumstances where the Mach number of the free-stream was 5 and the dynamic pressure was 33 kPa. The study indicates that the jets interaction effect dominates fairing’s aerodynamic characteristics in the separation process. The maximum coefficients’ variation of the normal force, axial force and pitching moment are 44.5%, 32.4% and 198.6% respectively. The pressure center moves forward obviously, making the fairing with designed static stability presents un-stability features in the minus attack angles. The influence of the separation distance on fairing’s aerodynamic characteristics becomes weaker as the separation distance increases. Using a small positive angle as the initial separation attack angle is helpful for the fairing maintaining a stable attitude, benefitting separation security during the separation process.
Simulation and fabrication of bionic sharkskin composite micro-nano wind resistance reduction structure
XU Zheng , LIU Ri etc.
 doi: 10.11729/syltlx20220002
[Abstract](521) [FullText HTML](165) [PDF 9375KB](37)
The combination of bionics and drag reduction technology has opened up an important research direction in the field of drag reduction, and has made a significant breakthrough. For better implementation to reduce the wind resistance effect, this paper studies the composite micro-nano drag reduction structure, according to the principle of bionics, through CFD simulation combined with the laser micro-nano fabrication technology. A combined model of drag reduction structure wad established. The flight vehicle air sensor head surface with bionic sharkskin composite micro-nano structures was manufactured by laser interfernce scanning on the basis of the bionic sharkskin scale structures, to further improve the drag reduction performance. Through the parallel simulation and wind tunnel test, the drag reduction mechanism was theoretically analyzed, and the composite structures were manufactured with a drag reduction rate of up to 10.3%.
A bi-weighted-POD and its application on wind pressure field
ZHANG Hao , YANG Xiongwei etc.
 doi: 10.11729/syltlx20210146
[Abstract](99) [FullText HTML](134) [PDF 7426KB](5)
Proper Orthogonal Decomposition(POD) is a reduced order modeling(ROM) method based on 2nd-order statics, which simplifies the investigated wind-pressure field in a new coordinate system formed by a set of orthonormal basis. This paper suggests a method of bi-weighted POD(which weights POD by area and at the same time by root-mean-square), and applies this method to the modal reduction of pressure field around buildings. Firstly, we introduce the POD expansion in a mean-square method, which demonstrates that POD is the optimal choice of ROM in the mean-square sense. Furthermore, we modify the original POD by the bi-weighting-method to improve its capacity of identifying coherent structures with lower energy in pressure field. For the last part, the validity of bi-weighted POD is roughly examined by a case study which applies the method to the pressure field of a 5∶1 rectangular cylinder. It turns out that the modified POD method improves the ROM accuracy at the area associated with lower energy in a significant way. In the meantime, a wind-pressure field ROM constructed by bi-weighted POD captures vital information provided by the original wind-pressure field and is spatially accuracy-consistent.
Experimental study on high frame rate characteristics of dynamic flow field of jet in crossflow
WANG Zhen , WANG Yayao etc.
 doi: 10.11729/syltlx20210077
[Abstract](227) [FullText HTML](90) [PDF 15431KB](22)
Despite the decisive influence of various vortex structures of a jet in crossflow on the jet trajectory and scalar mixing, there are few studies related to the high-frequency dynamic characteristics of shear-layer vortexes during transportation. This paper focuses on the high-frequency flow field characteristic, the scalar concentration distribution and the formation and collapse process of the turbulent microstructure of the jet in crossflow with different nozzle diameters and velocity ratios using 40 kHz particle image velocimetry(PIV) and 20 kHz acetone planar laser induced fluorescence(PLIF). The experimental measurements of the velocity and scalar field show that: increasing the velocity ratio promotes the expansion of the circulation zone behind the jet; in the near field of the jet trajectory, power law fitted velocity distribution and shear-layer vortex trajectory shows an exponentially decrease of the jet velocity, the shear-layer vortex strength and vortex motion frequency also show a downward trend, with the frequency of the shear-layer vortex on the windward side slightly lower than that on the leeward side; as the jet velocity increases, the frequency of the shear-layer vortex increases gradually, but the Strouhal number decreases.
Development of high-precision micro-rolling moment gas bearing balance
ZHANG Huangwei , XIANG Guangwei etc.
 doi: 10.11729/syltlx20210182
[Abstract](198) [FullText HTML](71) [PDF 6260KB](13)
During the reentry process of the miniaturized reentry vehicle, small asymmetry of its shape can be produced due to surface ablation, resulting in a small rolling moment. In order to obtain the high-precision micro-rolling moment measurement data of the ablation model of the miniaturized reentry vehicle in the hypersonic wind tunnel, and obtain the other five component aerodynamic data, a six component micro-rolling moment gas bearing balance was developed. The rolling moment design load of the balance is 0.02 N·m, and the axial force design load is 200 N, which are orders different from each other. The overall force measurement scheme of “4+2” balance is proposed, where the four component main balance elements cooperate with the two-component Mx-X elements to complete the extremely mismatched six component aerodynamic measurement. The results of the static calibration and the wind tunnel test show that the balance has good resolution and strong anti-interference ability, and is little affected by temperature. The measurement results of the rolling moment coefficient reach the order of 10–7. The developed gas bearing balance is little affected by the temperature and can be reused. It can measure the six components of aerodynamic data including the micro-rolling moment at the same time, which greatly improves the test efficiency and reduces the error caused by model disassembly.
A concise method of determining critical flutter wind speeds for small damping modes
TANG Jianping , HE Jun etc.
 doi: 10.11729/syltlx20210071
[Abstract](200) [FullText HTML](70) [PDF 6600KB](4)
In low speed flutter tests, flutter models with small damping modes start continuous vibration usually at low speeds without obvious flutter divergence. Therefore, it’s of some uncertainty on determing the critical flutter wind speeds by visual inspection or by “damping method (DM)” of modal parameter identification. Considering the similarity between the vibration phenomenon of a small damping modal flutter test and that of a fighter buffet test, a technique named “amplitude turning point method (ATPM)” similarly to that used in identifying buffet boundaries is proposed to determine the critical flutter wind speeds. The method is based on RMS of vibration amplitudes, the curves of normalized vibration RMS changing with wind speeds are drawn, and critical flutter wind speeds are determined according to the first turning points of curves. In a small damping modal flutter test, the method was applied in the test data processing of the engine hangers with variable parameters. Comparing the ATPM results with the DM results and the numerical results, the following conclusions are made: the results of three methods are in agreement, the ATPM results are more similar to the numerical results than the DM results, and the ATPM is concise and reliable, with good stability and applicability.
2023, 37(2).
Abstract(0) PDF(0)
Summary of research on flame 3D reconstruction based on computed tomography of chemiluminescence technology
FENG Xiaoou , JIN Yi et al.
2023, 37(2): 1-15. doi: 10.11729/syltlx20210148
Abstract(0) HTML(0) PDF(0)
Due to the characteristics of combustion such as three-dimension, high temperature, turbulence, and unsteady state accurate measurement of the combustion is difficult and is a hot research topic. Computed Tomography of Chemiluminescence (CTC) combines the chemiluminescence and CT technology. By directly shooting flame images from different angles and using reconstruction algorithms to reconstruct the flame, a fine description of the three-dimensional structure of the flame can be achieved quickly and accurately. The self-luminescence of the flame is used in the CTC as the light source, so there is no additional light source equipment required, which makes the system easy to build and can be implemented in a complex environment. These advantages enable the CTC technology to be used for real-time measurement of high temperature and turbulent flames, which is of great significance for studying complex combustion flow fields and improving combustion efficiency. In this paper, the basic principles of the CTC technology are introduced firstly, and then the research progress of the CTC technology in the direction of 3D reconstruction of flame is introduced in four aspects: the imaging model, the reconstruction algorithm, the experimental equipment and its application. Finally, the development trend of the CTC technology is discussed.
Experimental study on the effect of angle of attack on airfoil boundary layer
HAO Dongzhen , JIANG Nan et al.
2023, 37(2): 16-24. doi: 10.11729/syltlx20210117
Abstract(0) HTML(0) PDF(0)
In order to deeply understand the influence of the angle of attack on the airfoil boundary layer, a TR–PIV experimental study on the SD7003 airfoil is carried out. The distributions of statistics such as the average velocity of the airfoil suction surface and the Reynolds shear stress under the working conditions of the angle of attack α = 4°, 6° and 8° are compared. Proper orthogonal decomposition (POD) method is adopted for analysis of the experimental data. The flow structure in each mode and the frequency spectrum characteristics of the modes under different working conditions are analyzed in detail. The study finds that: with the increase of the angle of attack, the position of the separation bubble moves to the leading edge of the airfoil, and the thickness of the separation bubble increases; there is intensive shear motion inside the separation bubble and near the reattachment point; there are alternating positive and negative vortex structures near the reattachment point, and the vortex structures change continuously with the development of the boundary layer; the energy of each mode of POD decomposition is related to the scale of the structure contained and the mode frequency; with the increase of the angle of attack, the scale of the flow structures in the flow field increases, and the frequency domain distribution of flow field energy shifts from high frequency to low frequency.
The kinematics and performance of zebrafish C-shaped maneuvering
LIU Yuansen , YU Yongliang et al.
2023, 37(2): 25-35. doi: 10.11729/syltlx20210172
Abstract(0) HTML(0) PDF(0)
It is difficult to obtain the complete kinematics and hydrodynamics from the experiments in the study of fish C-type fast-start, which can be divided into C-start and C-turn by the duration of maneuvers. Using high-speed photography, a series of top-view images of zebrafish's C-shaped maneuvering were obtained on the self-built platform based on machine vision. A simplified three-dimensional (3D) fish model was established according to the outline and midline of the fish body extracted from the images by using a mathematical morphology algorithm. Then, due to the conservation of the linear and angular momentum, the complete kinematic and hydrodynamic data during the whole maneuver motion can be obtained and the translational and rotational energy can be distinguished from the total kinetic energy of the zebrafish body. The modification of the caudal fin length is a highlight in 3D modeling, which is based on the equivalence of the area second-moment of a flapping 3D plate. Through the benchmark validation, the maximum geometric error of the digital image processing is less than 3.1%. The results show that the maximum acceleration in all the C-type fast-start is linearly related to the maximum angular acceleration, and the rotational energy of C-turn is dominant in the kinetic energy while the translational energy of C-start is dominant.
Experimental study on generation of non-Newtonian droplets in dripping mode in a flow focusing microchannel
LIANG Dingxin , XUE Chundong et al.
2023, 37(2): 36-45. doi: 10.11729/syltlx20210184
Abstract(0) HTML(0) PDF(0)
Droplet microfluidic is an important branch of the microfluidic field and the biological fluids involved in it often have non-Newtonian properties. In order to understand the influence of non-Newtonian properties on droplet formation, four kinds of fluids with different rheological properties were configured to systematically study the non-Newtonian droplet formation in the dripping mode in a flow focusing microchannel. The results show that compared with Newtonian droplet formation, non-Newtonian droplet formation shows a more significant “beads-on-a-string” phenomenon. Different non-Newtonian properties have different effects on droplet formation. Shear thinning effect and elastic effect have opposite effects on the droplet size and formation frequency. The results of liquid column necking dynamics show that the process of liquid column necking is similar to that of Newtonian fluid due to a single shear thinning effect. The single elastic effect makes the capillary drive stage which appears of liquid column necking different from that of Newtonian fluid. The combined effect of the elastic effect and shear thinning effect leads to more significant capillary drive stage in the process of column necking and more significant “beads-on-a-string” after column necking.
Experimental study on influence of liquid depth on morphological characteristics after droplet impact
XU Duoguang , XU Wan et al.
2023, 37(2): 46-55. doi: 10.11729/syltlx20210153
Abstract(0) HTML(0) PDF(0)
Characteristics and mechanism of a droplet impacting on the liquid surface were studied experimentally. The process of droplet impinging on the liquid surface with different depths of the liquid pool was recorded with a high-speed camera, and the characteristic phenomena such as liquid crater, liquid crown, central jet and secondary droplet that appeared at different stages were summarized. An image processing program was developed and the automatic extraction of geometric parameters was then realized. The influence of pool depth Weber number, droplet diameter, and falling height on droplet impacts was discussed. The results show that: under the condition of constant Weber number, when the pool depth crosses a certain critical value, the characteristic phenomena such as liquid crater, liquid crown, central jet and secondary droplet change significantly; the ratio of the liquid crown height to the liquid crater depth increases within a certain range with the increase of Weber number; whether the secondary droplet can be separated by the central jet is closely related to the depth of the liquid pool and the diameter of the initial droplet.
Experimental study on drag reduction characteristics of biopolysaccharide solution
MENG Fanzhe , Qin Liping et al.
2023, 37(2): 56-61. doi: 10.11729/syltlx20210089
Abstract(1966) HTML(118) PDF(30)
In order to obtain the underwater drag reduction performance of the biopolysac-charide solution, the drag reduction characteristics of four biopolysaccharide solutions of guar gum, xanthan gum, tragacanth gum and locust bean gum were tested in the gravity circulating water tank experimental system. The influence law of the injection rate, Reynolds number and injection mass fraction on the drag reduction is shown. The results show that the four biopoly-saccharide solutions have significant spray drag reduction effects, and the locust bean gum solution has the highest drag reduction rate (14.3%). At a constant Reynolds number, with the increase of the injection rate, the drag reduction rate of each polysaccharide solution increases significantly, and shows different trends after reaching the peak value of drag reduction. The drag reduction effect of the polysaccharide solution is better when the Reynolds number is small (<2.0×104). With the increase of the Reynolds number, the drag reduction law of the polysac-charide solution shows differentiation. Excessive injection mass fraction would reduce the drag reduction effect of the polysaccharide solution, and increasing Reynolds number would cause the phenomenon of “peak shift” with the increase of the mass fraction. By introducing relative injection mass fraction, the effects of the injection rate, Reynolds number and injection mass fraction on drag reduction are coupled with each other. With the increase of relative injection mass fraction, the drag reduction rate of each polysaccharide solution increases first and then decreases. Finally, based on the injection spray mass fraction, the drag reduction law of the polysaccharide solution was explained preliminarily.
Computational investigation of unsteady heat exchange on regenerative cooling structure
ZHANG Ruoling , ZHANG Lei et al.
2023, 37(2): 62-67. doi: 10.11729/syltlx20210102
Abstract(0) HTML(0) PDF(0)
In order to support the regenerative cooling structure design and experiment of scramjet, an analytical model of unsteady heat exchange is constructed. The calculated and experimentally measured thermal equilibrium times under water cooling condition are compared. The calculated irregular temperature increasing time is obtained using the analytical model and compared with experimental values. It is found that the thermal equilibrium time can be decreased if the scramjet is preheated to 800 K before test. The research shows that the analytical model is applicable to heat transfer analysis of the regenerative cooling scramjet.
Practices and challenges on PIV technology in high speed complex flows
Liu Hong, Chen Fang, Li Xiaojie, Zheng Zhonghua, Xiao Baoguo
2016, 30(1): 28-42.   doi: 10.11729/syltlx20150069
[Abstract](297) [PDF 6594KB](42)
Experimental study on Reynolds number effect on aerodynamic pressure and forces of cylinder
Liu Qingkuan, Shao Qi, Zheng Yunfei, Li Conghui, Ma Wenyong, Liu Xiaobing
2016, 30(4): 7-13.   doi: 10.11729/syltlx20150112
[Abstract](352) [FullText HTML](114) [PDF 10428KB](12)
PIV measurement and numerical simulation of Taylor-Couette flow
Feng Junjie, Mao Yuhong, Ye Qiang, Liu Renhong, Chang Qing
2016, 30(2): 67-74.   doi: 10.11729/syltlx20150091
[Abstract](442) [PDF 5952KB](30)
采用粒子成像速度场仪(PIV)和数值模拟(CFD)对Taylor-Couette 流场进行测量,获得各转速下涡流场信息。将同等条件下PIV测量结果与数值模拟结果相联系,对比分析不同旋转雷诺数范围内涡流场中不同径线和中轴线上各向速度的变化特征。结果表明,各种特征存在一定的转速分段范围:在2~7r/min(Re为100~350)时,各向速度特征为层流涡特性,在7~40r/min(Re为350~2000)时,各向速度特征为波状涡特性,在40~60r/min (Re为2000~3000)时,各向速度特征为调制波状涡特性,当转速大于60r/min(Re大于3000)时,各向速度特征为湍流涡特性。根据不同角度获得的各向速度特征对应的内筒转速、旋转雷诺数与流场涡形态的关系,明确分析出特定几何条件下,泰勒涡发生形态转变的旋转雷诺数,以便于深入探究泰勒涡流场的特性,定量分析涡运动形态特征。
Review of research on the receptivity of hypersonic boundary layer
Jiang Xianyang, Li Cunbiao
2017, 31(2): 1-11.   doi: 10.11729/syltlx20160129
[Abstract](500) [FullText HTML](182) [PDF 7434KB](70)
Investigation of several fundamental combustion problems in rocket-based combined-cycle engines
He Guoqiang, Qin Fei, Wei Xianggeng, Cao Donggang, Huang Zhiwei, Liu Bing
2016, 30(1): 1-14,27.   doi: 10.11729/syltlx20150159
[Abstract](389) [PDF 6603KB](19)
Experimental study on the flow past a rotating cylinder with PIV
Sun Jiao, Zhang Bin, Tang Zhanqi, Chen Wenyi
2016, 30(1): 81-90.   doi: 10.11729/syltlx20150037
[Abstract](255) [PDF 4386KB](15)
投弃式海流剖面仪(Expendable Current Profiler,XCP)周围流场是典型的旋转圆柱绕流.探头周围流场对探头的运动状态起决定性作用,这直接关系到探头的测量性能,因此有必要对旋转圆柱周围流场进行实验研究.实验在循环水槽中进行,通过PIV对雷诺数保持不变(Re=1000)、不同圆柱旋转速度比(α=0、0.5、1.0、1.5、2.0、2.5、3.0、3.5、4.0、4.5和5.0)的圆柱下游尾流场进行研究.通过选取不同旋转速度比的任一时刻的瞬态流场,来分析旋转对圆柱尾流结构的影响.为了获得流场的频率信息,对所获得流场信息进行能谱分析来获取涡旋的脱落频率,并进一步使用正交模态分解对流场进行分析,给出了流场主要拟序结构及其能量与转速比的变化趋势.发现圆柱旋转改变圆柱尾流结构,使尾迹尺度变小.在旋转速度比0≤α≤2.0时,存在明显的周期性涡旋脱落,并且涡旋脱落的频率有逐渐升高的趋势;而且当转速比2.0<α≤5.0时尾迹流场的周期性减弱,涡旋脱落变得不明显,流场表现出低频、剪切层的区域特征.随着转速变大,涡旋尺度变小.在较高旋转速度比时,流场中能量被重新分布.
Measurements of circular cylinder's wake using time-resolved PIV
Wang Yong, Hao Nansong, Geng Zihai, Wang Wanbo
2018, 32(1): 64-70.   doi: 10.11729/syltlx20170099
[Abstract](422) [FullText HTML](253) [PDF 9648KB](27)
Experimental investigation on the aerodynamics of tunnel-passing for high speed train with a moving model rig
Song Junhao, Guo Dilong, Yang Guowei, Yang Qiansuo
2017, 31(5): 39-45.   doi: 10.11729/syltlx20170002
[Abstract](159) [FullText HTML](94) [PDF 10066KB](4)
Simultaneous OH and CH2O PLIF imaging of flame structures
Zhu Jiajian, Zhao Guoyan, Long Tiehan, Sun Mingbo, Li Qing, Liang Jianhan
2016, 30(5): 55-60.   doi: 10.11729/syltlx20160026
[Abstract](428) [FullText HTML](196) [PDF 7981KB](14)
OH和CH2O平面激光诱导荧光(PLIF)同时成像技术在研究火焰结构和燃烧反应中间产物二维分布等方面能够发挥重要作用。OH的分布被用来表征火焰反应区的结构,而CH2O的分布则被用来显示火焰预热区的分布。利用OH和CH2O PLIF同时成像技术研究了甲烷/空气部分预混火焰的结构。从实验系统、光路调节、时序同步、OH A-X(1,0)扫谱、数据采集和处理等方面讨论了PLIF同时成像技术的实验方法。实验结果表明,OH和CH2O PLIF同时成像能够分别呈现甲烷/空气部分预混火焰反应区和预热区不同形状的瞬时结构;由于反应区在相邻位置的结合,在火焰中能够局部生成新的分裂的预热区。
Effects of end plates on aerodynamic force of rectangular prisms in wind tunnel test
Zheng Yunfei, Liu Qingkuan, Ma Wenyong, Liu Xiaobing
2017, 31(3): 38-45.   doi: 10.11729/syltlx20170015
[Abstract](374) [FullText HTML](172) [PDF 1175KB](12)
A review on flow field velocimetry based on high-speed schlieren/shadowgraph systems
ZHU Haijun, WANG Qian, MEI Xiaohan, WU Yu, ZHAO Changying
2022, 36(2): 49-73.   doi: 10.11729/syltlx20210110
[Abstract](3107) [FullText HTML](573) [PDF 8779KB](573)
The 2-Dimensional (2D) and 3-Dimensional (3D) velocimetry based on schlieren/shadowgraph methods are reviewed in this article. The main content includes the basic optical setups and principles of schlieren and shadowgraph systems, as well as the velocimetry algorithms. For 2D measurement, there are mainly two types of velocimetry algorithms: one is cross-correlation algorithm adopted by PIV, while the other is the optical flow method. The basic formulas, advantages and limitations are introduced comparatively. A recent developed schlieren motion algorithm can provide high accuracy and dense estimation, which is promising and applicable in a wide range of applications. The 3D reconstruction and particle tracking algorithms highly rely on the systems. In this review, three different setups are introduced, including tomographic shadowgraphy, two-view collimated light path shadowgraphy and two-view converging path shadowgraphy. The two-view systems are more concise in setup, requiring less equipment, which are advantageous for high-speed measurements. The 3D particle tracking algorithms of two-view systems are introduced, while the main focus is placed on the image space-based tracking algorithms and the spatial-temporal tracking methods. The latter introduces the temporal predictions into the stereo matching process. The particle reconstruction and tracking correctness in dense particle situations is improved significantly by using the strongly coupled spatial and temporal constraints for optimisation. Its performance is superior to several artificial intelligence methods. The progress of the velocimetry algorithms, together with the imaging advantages of short exposure and high-frequency framing rate, has promoted schlieren/shadowgraph from conventional flow visualization to advanced velocimetry techniques, which can play a role for experimental study in a wide range of complex turbulent and transient flow conditions.
Recent advances in background oriented Schlieren and its applications
2022, 36(2): 30-48.   doi: 10.11729/syltlx20210173
[Abstract](2645) [FullText HTML](716) [PDF 7889KB](716)
Background oriented Schlieren (BOS) has appeared near 2000 as a variant of the classical schlieren technique. It is a new non-intrusive optical diagnostic technique for measuring the refractive index of complex flows quantitatively. Compared to knife-edge and rainbow Schlieren, BOS is advantageous in terms of optical alignment, systematic calibration, and the dimension of the field of view. The principle and the essential system parameters of BOS are introduced in detail. An overview of recent advances in the BOS technology is presented according to the typical sequence of setting up a BOS system. Finally, recent applications of BOS in super/hypersonic flows, combustion, and plasma flow environments are also introduced.
x Close Forever Close