2016 Vol. 30, No. 4

Fundamental Research and Application
Research on mechanism of transonic area rule in near field
Wang Ganglin, Zheng Sui
2016, 30(4): 1-6. doi: 10.11729/syltlx20160024
Abstract(162) HTML (119) PDF(6)
Abstract:
The qualitative descriptions of the area rule bring some confusion and problems to the actual aircraft design work. The linear perturbation assumption in conventional theoretical derivations does not suit the development for more and more refined aerodynamic design in the future. For AGARD-B standard model which has typical shape characteristics of high speed aircraft, we combined the CFD with optimization methods to probe the body modification form for optimal drag reduction. From that, a better drag reduction result and more detailed modification principles of drag reduction are obtained compared to those obtained from the traditional area rule method. Based on the present principles, through the analysis of drag force felt by each component and comparison of the drag forces on the body surface before and after modification, it is found that the essence of area rule drag reduction is the advantageous interference produced among the adjacent components of the aircraft configuration. Finally, the drag reduction effects of fuselage shrinkage cross-sectional shape are studied and verified. The comparison among different lift coefficient conditions validates that the drag reduction effect of area rule is the same under various lift coefficients and angles of attack condition.
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(591) HTML (201) PDF(23)
Abstract:
By wind tunnel tests, Reynolds number effect on drag force coefficient, lift force coefficient and wind pressure coefficient of cylinder were measured, the mechanism of the aerodynamic force variation from the point of view of the flow field distribution was analyzed, and the correlation of the flow field in the cylinder axis direction under the Reynolds number effect was studied. Results show that in the subcritical Reynolds number regime, the time averaged flow field around the cylinder model is symmetric, the Reynolds number has little influence on the averaged drag force coefficient and flow field, and the averaged lift force is around zero. In the critical Reynolds number regime, with the appearance of large amplitude negative pressure in certain areas, flow field becomes asymmetric, and the averaged lift force as well as fluctuation lift force appears. In the supercritical Reynolds number regime, with the appearance of large amplitude negative pressure on the two sides, flow field becomes to symmetric again, and the averaged lift force disappears. Reynolds number has obvious effect on the flow field correlation along the cylinder axis. In the subcritical Reynolds number regime, the scale of the Karman vortex in the cylinder axis direction is relatively large, while the scale becomes small with the increase of Reynolds number.
Experimental study on leak detection of cooling water in arc heater based on emission spectroscopy
Lin Xin, Chen Lianzhong, Dong Yonghui, Ou Dongbin, Li Fei, Yu Xilong
2016, 30(4): 14-19. doi: 10.11729/syltlx20150155
Abstract(194) HTML (126) PDF(3)
Abstract:
High-enthalpy arc heaters play an important role in the development of thermal protection materials and heat shield structures for entry vehicles because they are capable of producing longtime and representative flow environments. Owing to the large heat flux loading on the electrode, the erosion of the electrode is inevitable. Generally, high pressure water is used for cooling of the electrode. The arc heater may suffer serious damage caused by electrode leak, especially for hundreds or even thousands of seconds aerodynamic heating tests. Therefore, it is necessary to develop fast response diagnostic technique to monitor the operating status of the facility and determine the initial time of water leakage to avoid costly arc-heater failure. Because of the extreme conditions inside the arc-heater section, options for measurements of the test gases are limited, and optical spectroscopy-based measurements present a diagnostic opportunity. Optical Emission Spectroscopy (OES) is widely used for measuring gas parameters of high-temperature flow field because it is non-intrusive, high sensitive, and just constituted of simple instruments. In our studies, the 656.28 nm emission spectral line of the atomic hydrogen and the 777.19 nm emission spectral line of the atomic oxygen are utilized for routinely in situ monitoring the operating status and determining the initial time of water leakage at a high-enthalpy arc heater. According to the intensity ratio of the two emission spectral lines, the mass fluxes of the water leakage can be derived, which are 1.85~0.94g/s and 2.12~0.98g/s, corresponding to equilibrium temperatures equal to 6000~8000K and 5500~7500K under two different test conditions, respectively. The current test results of this study illustrate the feasibility and potential of the OES technology in high-enthalpy arc heater safety diagnosis, especially on the water leakage diagnosis.
Investigation on formation flight in wind tunnel
Liu Zhiyong, Tao Yang, Shi Zhiwei, Geng Xi, Yin Xiezhen
2016, 30(4): 20-25. doi: 10.11729/syltlx20150099
Abstract(225) HTML (132) PDF(12)
Abstract:
An investigation on two aircrafts in formation flight was conducted in 1m unsteady wind tunnel. The leading aircraft was supported by a tail sting which was jointed to a vertical vane rod mounted on a frame of axes to achieve different relation positions accurately (including longitudinal spacing, lateral spacing and vertical spacing). The following aircraft was supported by primary support system of the wind tunnel to change its angle of attack. The aerodynamic forces and moments were measured by an inner six-component strain-gage balance, and the interaction flow structures were measured by a PIV system. Two sets of models were involved. One was the simple wing-body configuration and the other was flying wing configuration. Results show that lift-to-drag ratio of the following aircraft changes remarkably as the wingtip vortex of the leading aircraft approaches the following aircraft's wing, and when the vortex is close to the following aircraft's wingtip, the following aircraft can obtain the maximum lift-to-drag ratio. The following aircraft's aerodynamic characteristics change remarkably as the leading aircraft's angle of attack increases. However, lift-to-drag ratio of the following aircraft changes little when its angle of attack is bigger than 8° even with the presence of the leading aircraft.
Numerical study of ground effects on high speed train aerodynamic drag
Zhou Jian, Ou Ping, Liu Peiqing, Guo Hao
2016, 30(4): 26-31. doi: 10.11729/syltlx20150124
Abstract(130) HTML (85) PDF(4)
Abstract:
Based on wind tunnel tests of aerodynamic drag on two kinds of 1/25th scale CRH2 models, research of aerodynamic drag with different experimental ground planes was carried out by numerical simulation. The reliability of the numerical methods was verified by comparing the results of simulation and tests. By analyzing the variation of the flow field and resistance distribution on the train body with the usage of the wind tunnel wall, the stationary ground plane, and the moving ground plane in simulation, it is found that: ground effects of different planes have a great influence on the drag measurement of the high speed train; the moving ground plane gives the best simulation performance; the results of drag computed with the other two ground planes are less than that with the moving plane and the difference increases with the increase of the body length, therefore, it is almost impossible to simulate the flow field of the real train operation. Finally the mechanism of influence by ground planes is analyzed and references are provided for drag measurement of high speed train on different ground planes.
The effect of detector installing structure on wall temperature measurement of vehicle
Shi Anhua, Shi Weibo, Sun Haihao, Liu Chunsheng, Han Dong, Huang Jie
2016, 30(4): 32-36. doi: 10.11729/syltlx20160021
Abstract(155) HTML (84) PDF(3)
Abstract:
The effect of the detector installing structure on the measured point temperature is analyzed using engineering aero-thermodynamics and heat conduction computation. To diminish the effect, a temperature detector installing structure is brought out according to the vehicle shell structure. The result shows that the installing structure has no effect on the measurement point temperature when the surface temperature is rising or heat is transmitting from the surface to the interior. However, the measurement temperature using the original installing structure is obviously lower than the predicted point temperature without the detector when heat is transmitting from the interior to the surface during the flight middle course. The temperature detector installing structure proposed in the paper can greatly reduce the structure effect on the measured point temperature:the maximum deviation of the temperature due to the presence of the detector is less than 0.5K.
Experimental and CFD study on the mechanism of supercritical airfoil drag reduction with micro vortex generators
Zhang Jin, Liu Jingyuan, Zhang Binqian
2016, 30(4): 37-41. doi: 10.11729/syltlx20150157
Abstract(172) HTML (95) PDF(8)
Abstract:
Wind tunnel and CFD methods are used to investigate the mechanism of the airfoil drag reduction with Micro Vortex Generators (MVGs). RANS and κ-ε turbulence model are used in CFD calculation. The results indicate that with MVGs, the bottom flow is directed to upper domains and thus the boundary layer flow is mixed. Therefore the averaged turbulence kinetic energy near the wall as well as the fluctuating pressure at the rear increases, so the pressure drag decreases. The gradient of the chord velocity and the turbulent viscosity decrease, but the gradient of the span velocity and fluctuating pressure increase more notably, so the turbulence stress increases and the frictional drag increases. MVGs are too small enough to be submerged in the boundary layer flow, and only mix the boundary layer flow. They have little influence on the height of boundary layer and the lift coefficient.
Test investigation of the aerodynamic characteristics of grid fins for configuration with body and fins
Song Shuheng, He Cao, Li Yonghong, Zhou Ling, Huang Yong
2016, 30(4): 42-47. doi: 10.11729/syltlx20140069
Abstract(178) HTML (106) PDF(9)
Abstract:
A wind tunnel test program is designed to investigate aerodynamic characteristics of different grid fins in subsonic and transonic flows, which has advantages of simple model design, avoiding installation of hinge moment balance on small models, and obtaining all aerodynamic forces and moments of grid fins. The aerodynamic characteristics of grid fins are analyzed, including simple frame configuration, upright honeycomb configuration and skew honeycomb configuration with different grid densities. The aerodynamic characteristics of different grid fins and planar fins are compared, and the influence of grid fin location on its aerodynamic characteristics is also investigated. The results show that grid fins and planar fins have respective advantages and disadvantages; the configuration, grid densities, and size of grid fins have an important impact on their aerodynamic characteristics. For different grid fins, the influence of location on its aerodynamic characteristics is not the same.
Experimental study on characteristics of the liquid holdup during mobile pipe draining
Jiang Junze, Zhang Weiming, Yong Qiwei, Jiang Ming
2016, 30(4): 48-55. doi: 10.11729/syltlx20150152
Abstract(181) HTML (101) PDF(2)
Abstract:
According to the structure of the steel mobile pipeline, a suit of liquid holdup detecting device with two capacitance probes is designed and manufactured based on the different permittivity values between the water and the gas. The device was applied to measure the liquid-holdup during mobile pipeline draining. Some results are found. First, the device is sensitive to the variation of liquid-holdup, so it can be used to measure the liquid-holdup during the draining online continuously, and the gas-liquid two phase flow pattern could also be judged by analyzing the liquid holdup variation. In addition, the liquid-holdup in the draining process is closely related to the gas pressure and flow rate. The higher the flow rate is, the more likely the slug flow occurs, the liquid-holdup is relatively low, and the gas percentage in the pipe is relatively high. On the contrary, the higher the pressure is, the lower the frequency and quantity of the slug flow occurrence are, and the liquid-holdup in the slug flow is relatively high. It shows that high pressure can increase the average liquid-holdup of the pipe, which is beneficial for keeping the pump working continuously and saving the time of draining.
MeasuringTechnique
Implementation and research on the reconstruction algorithms of pressure fields based on PIV
Liu Shun, Xu Jinglei, Yu Kaikai
2016, 30(4): 56-65. doi: 10.11729/syltlx20150119
Abstract(229) HTML (138) PDF(45)
Abstract:
The basic principles and the corresponding algorithms of the finite volume method, the direct integral method and the Poisson equation method are introduced in detail, which are used to reconstruct the pressure fields based on PIV velocity fields. The instantaneous velocity fields of two incompressible flows, including the pipe flow with a sudden expansion and the flow around a square, are selected to study the influence of picture noise, velocity error, interpolation methods, the type and the precision of boundary conditions on reconstructed pressure fields by using different reconstruction algorithms. Finally, the transient pressure distributions of the pipe flow with a sudden expansion at 20ms are obtained by using the three algorithms respectively as well as the CFD. It shows that the finite volume method and the direct integral method are easily affected by noise to produce rude shocks, but maintain high accuracy in a larger range of error in velocity fields while they can get higher precision of reconstructed pressure fields with bilinear interpolation; the Poisson equation method isn't easily affected by noise so it produces few shocks, and has great advantages with the accurate PIV velocity fields while it can get higher precision of reconstructed pressure fields with bicubic interpolation; by measuring only several pressure points on the boundaries, the mixed boundary condition gets the accurate reconstructed pressure fields which are close to those of the Dirichlet boundary condition and far better than those of the Neumann boundary condition; the error of boundary conditions reduces the precision of reconstructed pressure fields, which is more severe than the error of velocity fields.
Development and application of the force-measuring balance in impulse combustion wind tunnel tests
He Wei, Gao Chang, Zhang Xiaoqing, Yu Shien
2016, 30(4): 66-70. doi: 10.11729/syltlx20160011
Abstract(389) HTML (160) PDF(13)
Abstract:
A design scheme of strutting internal six-component strain gage balance is developed to meet the requirements of aerodynamic load tests for big-weight hypersonic models under cold and hot conditions in the impulse combustion wind tunnel. The fast-response ability of balances is crucial in hypersonic force-measuring tests because of short test duration, serious impulsive load and big model weight. The mutually exclusive stiffness and sensitivity are coordinated. The balance is qualified according to static calibration results. Demonstrated by the test results, the consistency between the output signal of the balance and the combustor pressure is good, which indicates that the balance accurately reflects the aerodynamic loads of the model. Stability of the balance is confirmed by the axial force coefficient precision of 1.6% in the repeated calibration tests, and the eigen frequencies of the axial force, normal force and pitch moment signal satisfy the criteria in impulse wind tunnel tests. In conclusion, the balance has met the requirements of aerodynamic load tests of hypersonic vehicle models in impulse combustion wind tunnels.
Study on model base pressure measuring technique in hypersonic wind tunnel
Xie Fei, Guo Leitao, Zhang Shaowu, Cao Cheng, Zou Qiongfen
2016, 30(4): 71-75. doi: 10.11729/syltlx20150043
Abstract(139) HTML (84) PDF(7)
Abstract:
It is an experimental technique problem to exactly achieve test model base pressure in hypersonic wind tunnel. Because of the large error of model base pressure measurement before, it is difficult to exactly deduct the model base drag. Three base pressure measuring methods are developed in Φ1m hypersonic wind tunnel, viz. the absolute pressure micro-sensor measuring method, the low pressure differential pressure sensor measuring method and the electronic scanning pressure (ESP) measuring method. The validation tests of HB-2 standard model and a certain missile model are separately conducted at Ma=6. The test results indicate that: the absolute pressure micro-sensor measuring method can avoid the influence of piezometric pipe; it also can rapidly respond the variation of model base pressure with high accuracy.
Study and development of total pressure probe and pitot tube in 3m×2m icing wind tunnel
Zu Xiaoyong, Zhang Lin, Xiao Bin, Zhu Shimin
2016, 30(4): 76-80. doi: 10.11729/syltlx20160006
Abstract(263) HTML (119) PDF(15)
Abstract:
The total pressure probe and the pitot tube with the anti-icing/deicing functions are important measurement equipment in icing wind tunnels for which the aerodynamic design is critical. Taking a cue from some airspeed head's manufacture, the total pressure probe and the pitot tube are designed, by using new techniques and deploying the proper heated cable distribution. They show reasonable results in the ground-based static testing, calibration and experiment in the icing wind tunnel with high reliability and insulating property according to China national military standard.
ExperimentalEquipmentandMethod
Research on key technologies of debugging and operating in 0.6m×0.6m continuous transonic wind tunnel
Xiong Bo, Zhou Enmin, Cheng Song, Zhang Wen, Liu Kai, Luo Xinfu
2016, 30(4): 81-86. doi: 10.11729/syltlx20150052
Abstract(177) HTML (88) PDF(10)
Abstract:
In order to reduce the risk of constructing a large-scale continuous wind tunnel, research on key technologies is carried out in the 0.6m wind tunnel of China Aerodynamics Research and Development Center, such as anti surge control and speed control of the compressor, Mach number control, and so on. Pressure fluctuation method is used to measure the surge margin of the compressor accurately, and the security of the compressor can be well ensured by setting a reasonable alarm line and surge line. Vector control technology is used to achieve the accurate control of speed, and the 0.03% control precision is achieved. The accurate control of Mach number is achieved by the function relationship between the compressor speed, chamber flow, the centrosome displacement and the Mach number, and the 0.002 control precision is achieved. Through the research of the key technologies, the operation mode of fixing stagnation pressure and Mach number is realized. Due to the excellent quality of flow fields achieved in the wind tunnel, it is a good platform to carry out basic and leading research on the construction of large continuous wind tunnels.
The design of total pressure control strategy for 0.6m continuous transonic wind tunnel
Li Zhuangsheng, Yang Pengcheng, Chen Dan, Zhang Yongshuang, Guo Shouchun, Chen Tianyi
2016, 30(4): 87-92. doi: 10.11729/syltlx20150129
Abstract(156) HTML (73) PDF(10)
Abstract:
The total pressure is one of the key indicators of the continuous tunnel control system, the control precision and speed of which are very important to improve the efficiency of wind tunnel test and reduce energy consumption. The 0.6m wind tunnel is the first domestic continuous transonic wind tunnel with the negative pressure test ability, which can provide lots of test conditions covering wide total pressures. Based on its pressure condition, the total pressure control strategy is designed, and the different control ways of valve combination are ascertained depending on the different pressure conditions. Meanwhile, the control algorithm of segmented parameters combining with the fuzzy PID is proposed, to improve the poor adaptability of fuzzy PID to the wide pressure range and multi-adjustment condition in continuous transonic wind tunnels. In our algorithm, the reasonable benchmark parameters P and I under the different segmentation interval due to the target total pressure should been determined firstly. Then it would been modified by fuzzy control algorithm. The result shows that the total pressure control accuracy is better than 0.1%, and the control strategy can adapt to the control requirement of different working conditions.
Investigation on the flow rotation effect and elimination in hypersonic wind tunnel
Chen Aiguo, Li Xuguo, Mao Chunman, Sun Liangbao, Long Yongsheng, Yang Yanguang
2016, 30(4): 93-96. doi: 10.11729/syltlx20150146
Abstract(131) HTML (81) PDF(9)
Abstract:
Wind tunnel experiments require high quality flow field,but in some hypersonic wind tunnel,the inlet flow may be rotated for preventing the local overheating of the heater.In order to eliminate the rotation,a reverse rotating flow is added into the main stream before the stability section of the wind tunnel.A wing model and a high precision roll balance were designed to study the total effect of the flow rotation in the hypersonic wind tunnel.The rolling moment measurements are carried out in the Φ0.3m hypersonic low density wind tunnel of CARDC under the test conditions of Mach 6, stagnation pressure of about 2×105Pa and room temperature nitrogen.The results show the rotation exits and the maximum rolling moment coefficient is 1.657×10-3;Reverse flow of about 2% total flow flux can reduce the rolling moment coefficient by 2 orders of magnitude. It is proved to be an effective solution for improving the quality of the wind tunnel flow field.
Design of nozzle inviscid contour based on axial Mach number distribution
Hu Zhenzhen, Li Zhenqian, Shi Yilei, Chen Aiguo
2016, 30(4): 97-104. doi: 10.11729/syltlx20150115
Abstract(202) HTML (168) PDF(23)
Abstract:
The supersonic inviscid contour design methods were studied for the hypersonic wind tunnel axial-symmetric nozzle. The Direct-design technique based on the axial Mach number distribution presetting was introduced, the axial Mach number distribution presetting method based on the ratio of area was improved, and a new multipoint-control characteristic point distribution method was proposed. The designed nozzle characteristic network was triangulated and compared with the numerical simulation result, and influencing factors were analyzed for the nozzle inviscid contour. Results indicate that: the feasibility of the axial Mach number distribution presetting method based on the ratio of area is guaranteed by the present improvement; the nozzle inviscid contour is significantly affected by the axial Mach number distribution, axial characteristic point distribution and the amount of characteristic points on the boundary.