2015 Vol. 29, No. 2

Display Method:
Progress of videogrammetric measurement techniques for high speed wind tunnel test
Zhang Zhengyu, Huang Xuhui, Yin Jiang, Zhou Run, Gao Feng, Li Duo
2015, (2): 1-7. doi: 10.11729/syltlx20140070
Abstract(127) PDF(7)
Abstract:
Videogrammetric measurement for wind tunnel test is research focus at home and abroad because it has no special requirements on the test model.The key technical progresses of the videogramnetric measurement for the vibration environment of the high speed wind tunnel are introduced in this paper,such as the solution of exterior parameters in big-angle large overlap, the algorithm of image processing for extracting marked point,the method of camera calibration and wave-front distortion field measurement.The great application prospects of videogrammetric measurement in 2m size high-speed wind tunnel test are demonstrated by several practical cases, which show that the precision of the videogrammetry is high,that is,the standard deviation of angle of attack is equal to or smaller than 0.0075°;the standard uncertainty of the deformation data is 5.232±0.082mm;videogrammetry provides a new way to research on and measure aero-optic effects.The method which is simple and does not require expensive coherent light sources.
Calibration of MEMS wall shear-stress-sensors array for underwater applications
Tian Yukui, Xie Hua, Huang Huan, Sun Hailang, Zhang Nan, Shen Xue
2015, (2): 8-12,25. doi: 10.11729/syltlx20140109
Abstract(111) PDF(4)
Abstract:
The measurement of wall shear stress on hydrodynamic surface is important for the design of advanced naval technology,and,accurate calibration,especially the static calibration, of the shear stress sensor is indispensable to any practical measurement.In the paper,an under-water calibration apparatus is developed based on analyzing the existing calibration methods.CFD simulation is performed to predict the wall shear stress input for the static calibration,and facili-tate the design of calibration schedule.Then a typical thermal MEMS shear-stress-sensors array is statically calibrated for underwater applications.The calibration coefficients of the sensors in the array are obtained in situ,which would be of use to the future underwater model tests.
Experimental investigationon the aerodynamic heating to tile-to-tile gaps in tubulent bouandry layer
Gong Hongming, Chen Jingqiu, Li Li, Tian Runyu
2015, (2): 13-18,25. doi: 10.11729/syltlx20140093
Abstract(115) PDF(6)
Abstract:
The characteristics of aerodynamic heating on tile-to-tile gaps in the flow of Mach number 6.1 with Reynolds number of 6.2×10 7/m was investigated in shock tunnel.Thermal in-sulating tiles and tile-to-tile gaps,arranged in T style and + style,were simulated on a flat plate model.Turbulent boundary layer was obtained upstream of the tile gaps by using a grit strip near the leading edge of the flat plate.Heat transfer was measured at the foward faces,side faces and the bottom surface of these gaps,and also at the tiles’surface.The effect of external flow angu-larity,gap width,gap depth and misalignment between tiles on the heating distribution in gaps was also examined.Experimental data reveal that the peak heating is most likely to appear on the gap top edges,especially on the forward face at the T-crossing,where a localized peak heating with amplitude approximately 11.6 times larger than that of the flat plate case was measured.It is also indicated that both the localized peak heating and the overall heating are reduced when the flow angle is adjusted to be 30°~60°,and are raised with the increasing gap width and tile-to-tile step height.
Study of surface heat transfer characteristics of hypersonic flat plate with film-cooling structure under different leading edge shape conditions
Wang Xiaohu, Yi Shihe, Fu Jia, Lu Xiaoge, He Lin
2015, (2): 19-25. doi: 10.11729/syltlx20140099
Abstract(179) PDF(12)
Abstract:
For an aircraft equipped with the infrared imaging homing seeker flying at hyper-sonic speed inside the dense atmosphere,some active cooling methods are needed to prevent the areothermal aberration caused by serious aerothermal heating and the aero-optical effect caused by the complex flow field.Based on the effect of both hypersonic blunt body flow and film cooling structure (i.e.supersonic backward step with slot at step base),the characteristics of surface heat transfer distribution over the hypersonic flat plate with a film cooling structure under differ-ent leading edge shape conditions are studied.The tests are implemented on the KD-01 hypersonic gun tunnel,and the heat flux in the downstream region of the slot under Mach 8 free stream condition is measured.The NPLS images of the instantaneous flow field around the slot of hyper-sonic flat plate with the film cooling structure (when the cooling film is laid idle)are obtained for different leading edge shape situations.Based on the analysis of the test data,it is concluded that:for the hypersonic flat plate with a film cooling structure (when the cooling film is laid idle),the leading edge shape has a distinctive influence on the distribution of surface heat flux;for the blunt leading edge,the surface heat flux is close to the analytical result of heat flux of the laminar boundary layer of a flat plate with the same leading edge shape;for the sharp leading edge,the heat transfer features develops from laminar to turbulent status;the heat transfer features in the separation and r eattached region downstream of the slot depend on the relative boundary layer thickness at the slot lip,which is similar to the situation of a common supersonic step flow.
Experimental and numerical study on hydrodynamic characteristics in water-exit of slender body
Chen Bo, Peng Libing, Shi Honghui, Jia Huixia
2015, (2): 26-31,42. doi: 10.11729/syltlx20140050
Abstract(157) PDF(17)
Abstract:
The water-exit process of a vehicle involves severe gas-liquid mixing,and the flow field is unsteady and highly nonlinear.To understand the characteristics of the process,the water-exit process of high speed slender body is studied by experimental and numerical simulation.The experiment was operated in a two-dimensional water tank,and the flow field of the water-exit of a slender body with different velocities was photographed by a high speed camera.The water-exit process according to the experiment was simulated,the Volume of Fluid(VOF)model was used to simulate the interface between water and air,and the dynamic mesh and UDF technology were adopted to simulate the movement of the slender body.The growing process of the cavity,the mechanism of the cavity collapse,and the way of the slender body affecting the free surface when the slender body moving in the water have been investigated.The experimental result indicates that:(1)there is a sudden increase in velocity when the slender body completely leaves water;(2)as the velocity increases,the cavity phenomenon begins to appear at the end of the slender body,and subsequently appears at the head of the slender body;(3)if the velocity is not large enough to generate local cavity at the head of the slender body,the free surface uplifts obviously as the slender body exits from the water.If the local cavity appears at the head of the slender body,the free surface uplift phenomenon is unobvious,and the “splash”phenomenon appears. The numerical result indicates that the free surface uplift phenomenon endures for the whole water-exit process,and the extent of free surface uplift is larger when the tail leaves water than the head.The numerical result was found to be in agreement with the experimental results.
The atomization characteristics research for spray nozzle of icing wind tunne
Fu Cheng, Peng Qiang, Zhang Haiyang, Wang Chao
2015, (2): 32-36. doi: 10.11729/syltlx20140058
Abstract(160) PDF(16)
Abstract:
The icing cloud inside the icing wind tunnel test section is generated by the Spray Bar System (SBS)which is located at the wind tunnel settling chamber.The icing conditions such as the icing cloud liquid water content (LWC)and the water droplet size (MVD)are deter-mined by the spray nozzle performance of SBS.In this paper,the droplet size distribution and the water flux of the small droplet spray nozzle used in the icing wind tunnel are measured on a spray testing platform by Phase Doppler Interferometer(PDI)and low flow rate flow-meter.The for-ward scattering method was used to optimize the quality of the PDI signal and the reliability of the result.The influence of the water pressure,the air pressure,their difference and the throttle pipe diameter on the atomization characteristics of the spray nozzle are investigated.The results show that:when the pressure difference between water and air increases,the MVD and water flow-mass also increases;as the diameter of throttle pipe of water is reduced from 0.4mm to 0.35mm,the range of pressure difference between water and air increases,and the coverage of the water practical size and flow mass can exactly meet the icing wind tunnel operation require-ments.The water flow-mass ratio of the spray nozzle can reach 11.5 and the droplet diameter range can vary from 7μm to 70μm,which are better than the other similar icing wind tunnel spray nozzles in the world.
Research on interference effects of wind load on bundled conductors
Zuo Taihui, Niu Huawei, Min Xuan, Hua Xugang
2015, (2): 37-42. doi: 10.11729/syltlx20140060
Abstract(142) PDF(4)
Abstract:
It is important to take into account the drag coefficient and interference shielding effect under different wind conditions in the design of bundled conductors.However,it is a com-plex problem under different wind angles and Reynolds numbers conditions.In this paper,wind tunnel test on a sectional conductor model with 1m long and 1:30 aspect ratio was firstly conduc-ted to investigate the influence of Reynolds number and wake effect on the mean drag coefficient of bundled conductors.Then,sectional model tests of 4-,6-and 8-bundled conductors under dif-ferent wind attack angles and velocities in the uniform flow were conducted to analyze the shiel-ding effect of drag coefficient of bundled conductors.The results indicate that the interference shielding effect is evident for multi-bundled conductors.In addition,the variation of the wind attack angle has great effect on the wind loads,the values of which are obviously smaller than that of the current design specification.Therefore,it is of great importance to pay attention to the influence of the wind attack angle and interference shielding on the wind load computation in the design of bundled conductors.
Research on asymmetric field flow in the subsonic second throat
Meng Fanmin, Zhang Ren, Li Qingli, Cui Xiaochun
2015, (2): 43-47. doi: 10.11729/syltlx20140061
Abstract(138) PDF(4)
Abstract:
China will consider the construction of large transonic wind tunnels and develop fi-ner wind tunnel test simulation techniques to meet the needs of future advanced aircraft develop-ment.As an effective means to control the Mach number,the second throat is considered to be one of the key technologies to enhance the ability of transonic wind tunnel.In this paper,we i-dentify the asymmetric field flow in the second throat by the CFD simulation.Then we design and manufacture a new second throat section with variable center subject for the model wind tun-nel.The wind tunnel test results show that the asymmetriy field flow occurs in the second throat when the total pressure reaches a certain value,which can be forward transmitted to affect the quality of the test section flow.Finally,we design a new kind of second throat which would not generate the asymmetric field flow by the CFD method.
Research on optimizing vortex-induced vibration performance for suspension bridge based on section model test
Zhang Jian, Zheng Shixiong, Tang Yu, Wang Qi
2015, (2): 48-54. doi: 10.11729/syltlx20140037
Abstract(150) PDF(4)
Abstract:
In view of the flat steel box girder which is a commonly used form of main girder cross section,in order to investigate its vortex-induced vibration(VIV)performance,and propose effective mitigation measures,a long span suspension bridge with steel box girder was taken as an engineering example.The section model,whose scale ratio is 1/50,was employed in XNJD-1 (was employed in uniform stream wind tunnel tests).The effects of wind attack angle,damping ratio and guide vane on VIV response were investigated in detail.However,the effects of pave-ment railings and maintenance tracks on VIV response were just briely discussed as on auxiliary research object of this paper,because pavement railings and maintenance tracks are requisite at-tachments to the bridge section in the completion state and large amounts of research results have already shown that the influence of their geometrical modifications and locations on VIV response of the main girder cross section can′t be obviously mitigated.Finally,the effective aerodynamic optimization measures were presented to reduce the VIV response in a series of studies,providing valuable reference for VIV response suppression study for similar bridge section in the future. The research results show that the locked velocities and amplitudes of VIV change with the wind attack angle,and increasing damping ratio can obviously reduce the torsional amplitude of VIV, and less obviously reduce the vertical amplitude of VIV.Removing the pavement railings or maintenance tracks can obviously reduce the amplitudes of VIV and improve the velocities of the first vertical vibration and the torsional vibration,and sometimes even eliminate the VIV response.Above all,the VIV response of this bridge section,whose wind fairing is short and blunt, can be effectively suppressed by installing the wide guide vane at the wind fairing,but the suppres-sion would be ineffective if the wide guide vane is installed at the beam bottom.Furthermore,the structure of this measure is relatively simple so it can be convenient for engineering purpose.
Three-dimensional PIV measurement technique for complex solid boundary:arbitrary three-dimensional boundary recognition algorithm
Chen Jian, Shi Shengxian, Liu Yingzheng
2015, (2): 55-61,67. doi: 10.11729/syltlx20140150
Abstract(192) PDF(12)
Abstract:
A SURF based three-dimensional boundary recognition algorithm has been devel-oped for identifying and reconstructing three-dimensional geometry of arbitrary solid boundaries. This method is used in conjunction with MLOS-SMART three-dimensional particle image recon-struction and three-dimensional cross-correlation algorithms to simultaneously measure the veloc-ity field as well as the boundary geometry.The boundary recognition algorithm was firstly veri-fied by using a set of cylinder images where the exact curvatures were known.The three-dimen-sional velocity field of a cylinder wake was then calculated by CFD and used for generating syn-thetic particle image sets.Finally,the validity and accuracy of the algorithms were verified by processing the synthetic images and comparing the calculated velocity filed and boundary geome-try with CFD data and the exact cylinder dimensions.
Application of surface-heat-flux estimation by measuring model interior temperature in hypersonic wind tunnel tests
Zhang Shiyu, Zhao Xuejun, Chen Zelin
2015, (2): 61-67. doi: 10.11729/syltlx20140089
Abstract(131) PDF(10)
Abstract:
A series of hypersonic wind tunnel tests are implemented to estimate the aero-heat-ing flux of a test plate.The heat flux at the heated surface is not directly measured,but is esti-mated by solving an inverse heat conduction problem (IHCP)based on measured temperature at the back surface or inside of the plate.The most outstanding advantage of this method is that the temperature sensors do not contact with the high temperature outflow directly,but are embed ded inside the plate.Therefore,it provides an alternative approach to estimate the high tempera-ture surface heat flux for practical hypersonic vehicle flight tests.The primary aim of this paper is to verify the applicability of this method to predict the flow characteristics of the outflow filed. The hypersonic wind tunnel tests are implemented in FD-03 WT of China Academy of Aerospace Aerodynamics (CAAA).Some tests apply a smooth plate in general hypersonic wind tunnel tests;and others adopt a test plate bounded with a trip line to interrupt the boundary layer of the plate.As shown in the heat flux estimated results,severe changes in the outflow such as shock waves caused by the trip line can be predicted by the estimated heat flux.
Study on flowrate measurement model of gas-liquid two-phase flow by using double-cone flowmeter
Xu Peng, Xie Dailiang, Zhang Lingfeng, Chen Panpan
2015, (2): 73-78. doi: 10.11729/syltlx20140031
Abstract(141) PDF(2)
Abstract:
Gas-liquid two-phase flow is encountered in chemical,power engineering,petrole-um refining,energy conversion and other industries.The parameter measurement and behavior investigation of two component flow are problems difficult to avoid for monitoring industrial sys-tems.A new flow sensing method based on a differential pressure flowmeter of a double cone structure is proposed.The new double-cone flowmeter is developed based on the V-Cone flowme-ter,which has advantages of simple and stable structure,convenient processing,and not easy to wear,etc.Five double-cone flowmeters with different diameter ratios which are 0.5,0.6,0.7, 0.8 and 0.9 are designed and manufactured.The measurement characteristics of the flowmeters for the single flow are analyzed.The total mass flowrate of gas-liquid two-phase flow is measured using the differential pressure signals.The experimental studies are conducted on the gas-liquid two-phase flow in the horizontal pipe by using the five new double-cone flowmeters.Through a-nalysis of the relationship between Lockhart-martinelli number and prospective gas flow ratio, the total mass flowrate measurement models for the total mass flowrate of gas-liquid two-phase flow are established on the basis of separated flow theory.The experimental results show that the prospective gas flow ratio has a good linear relation with the Lockhart-martinelli number. And the coefficients of the models are obtained through linear fitting.The seperated model,the Murdock model,the Lin model and the proposed models are applied to measure the total mass flowrate,and the measurement errors are analyzed and compared.The results show that the pro-posed models are more suitable than the other three models for the new doble-cone flowmeters that the total mass flowrate measurement errors of the proposed models can be within 6%.These results show that combined with the new proposed models,the new double-cone flowmeters per-form well in the flowrate measurement of the air-water two-phase flow.
Nitric oxide concentration and temperature measurement for shock tunnel free stream using mid-infrared absorption spectroscopy
Zeng Hui, Yu Xilong, Li Fei, Zhang Shaohua
2015, (2): 79-83. doi: 10.11729/syltlx20140044
Abstract(200) PDF(17)
Abstract:
In this paper,JF-10 shock tunnel is driven by H2/O2 detonation and the free-stream contains some trace components which are generated by non-equilibrium processes such as ionization and dissociation.Tunable diode absorption spectroscopy (TDLAS)is used for tempera-ture and concentration measurement of nitric oxide in the free-stream and this quantitative meas-urement is helpful to understand the non-equilibrium processes.In the experiments,the test sec-tion’s static pressure of JF-10 shock tunnel is just several hPa.Thus,Doppler broadening domi-nates,which is caused by random thermal motion of the absorber species.The half width of Doppler broadening is temperature dependent and this functional relation provides a method for gas temperature and species concentration measurement.A mid-infrared quantum cascade laser of 5.2μm central wavelength is used and gas temperature and nitric oxide concentration are meas-ured using a single line of 1909.7cm-1 wavelength by direct absorption-wavelength scanning method under 2kHz scanning frequency.The measured partial pressure of nitric oxide is about 0. 33Pa which represents its concentration and the temperature is about 600K in the free-stream.
Experimental and numerical simulation studies on heat flux measurement for slug calorimeters in the conduit
Xu Kao, Chen Lianzhong
2015, (2): 84-89. doi: 10.11729/syltlx20140127
Abstract(132) PDF(3)
Abstract:
The slug calorimeters in the supersonic turbulent conduit of the arc heated wind tunnel were improved.The line-contact calorimeter and the calorimeter which has a 0.4mm gap betwenn the heated end brim of the slug and the test article are adopted.Comparing to measured heat flux data by the typical slug calorimeters,the experimental results show that the output characteristics of the three types of calorimeters have good consistency under the condition of low pressure and low cold-wall heat flux;as pressure increases,the measurement values of the line-contact calorimenters slightly decrease and the measurement values of the 0.4mm gap calorime-ters increase noticeably.To explain the result,the flow characteristics of the 0.4mm gap clorim-enters are investigated.The influence of the free stream Mach number on the flow in the gap is also studied.
Studies on principles of long-running shot tunnel driven by opposite compression piston drivers
Long Tiehan, Xu Shengli
2015, (2): 90-96,102. doi: 10.11729/syltlx20140043
Abstract(225) PDF(5)
Abstract:
The theoretical basis of the long-running shot tunnel driven by opposite compres-sion pistons is laid.The long-running shot tunnel driven by opposite compression pistons can provide long-lasting high enthalpy and high pressure experimental gas flow,which is a new idea to build long-running hypersonic tunnels.The operation principles of the long-running shot tun-nel driven by opposite compression pistons are analyzed by theoretical simplification and computa-tional fluid dynamics to validate its feasibility.In theoretical analysis,based on the uniform flow field assumption,the test time and the time histories of pressure and temperature are presented with the consideration of the specific heat at constant pressure changing with temperature.The operation of the tunnel is simulated numerically by commercial code Fluent.The results indicate that the pressure of the experimental gas can be kept nearly constant with pressure stabilizer by extruding for about 25 microseconds,that is consistent with theoretical analysis results.Because of the compression of the opposite pistons,the temperature of the flow field is non-uniform and the temperature fluctuation amplitude is less than 180K.This is a notable problem of long-run-ning shot tunnel driven by opposite compression pistons that needs to be resolved.
Development of acoustic measurement system for wind tunnel
Lu Xiangyu, Bo Lin, Wen Yuchang, Chen Zhengwu
2015, (2): 97-102. doi: 10.11729/syltlx20140057
Abstract(173) PDF(8)
Abstract:
The acoustic measurement system is an important component of the in 5.5m×4m large-scale low-speed aeroacoustic wind tunnel,which is mainly used to accurately identify the ar-ea upon the test model where the aerodynamic noise is generated and measure the background noise of the wind tunnel under different conditions.According to the current status of the acous-tic measurement technology at home and abroad,combined with the specific requirements of aeroacoustics test,a high performance acoustic measurement system has been developed to per-form accurate measurement of aerodynamic noise source location and wind tunnel background noise.Test results show that the measurement system can meet the test requirements in the acoustic wind tunnel.Distributed structure greatly improves the reliability and SNR of the sys-tem.Plug and play technique effectively reduces the construction,configuration and programming work to improve the flexibility and configurability of the system.Multi-threaded parallel processing algo-rithm and TDMS technology can realize the real-time streaming data up to 153.6MB/s,and the packet storage technology provides a guarantee for the orderly storage and fast retrieval of massive data.
Research on ventral support interference correction for airship model
Huang Xia, Li Guoqiang, Huang Zongbo, Wang Xunnian, Zhu Minghong
2015, (2): 103-107. doi: 10.11729/syltlx20140084
Abstract(187) PDF(4)
Abstract:
The wind tunnel test and numerical calculation of ventral support interference for a rigid airship model are conducted in this paper.In the wind tunnel test,the one-point ventral support system is used for sustaining the airship model,the aerodynamic data are acquired,and the support interference values are obtained by the two-step mirror method.However,in the test the secondary interference between the main support and the mirror support can not be deducted, which would bring some errors to the support interference correction.So the numerical method is introduced to calculate the aerodynamic properties in the situations of airship model only,model with support,reverse model with support,and reverse model with main support and mirror sup-port,respectively.Based on the work,the net support interference and the secondary interfer-ence are acquired.By comparing the test and numerical results,some conclusions are drawn as follows:the test and numerical results are consistent about the way in which the support affects the airship aerodynamic properties,but there are obvious differences in the interference values, which shows that the secondary interference can not be ignored and must be considered in the process of support interference correction for the airship wind tunnel test.
测量技术
TDLAS 技术二次谐波法测量发动机温度
Tao Bo, Wang Sheng, Hu Zhiyun, Zhang Lirong, Zhang Zhenrong, Ye Xisheng
2015, (2): 68-72. doi: 10.11729/syltlx20140053
Abstract(20) PDF(7)
Abstract:

发动机燃烧流场温度的准确实时诊断对研究燃烧机理、提高燃烧效率及降低污染物排放等至关重要。分析了 TDLAS 技术二次谐波法免标定测温原理,实现了利用该技术对直联式超燃冲压发动机燃烧室内部温度的在线测量,并采用电控平移台扫描的方式实现了发动机出口与扩张段温度随空间变化的测量。结果表明该发动机燃烧特性主要有:(1)发动机出口与扩张段,氢气与乙烯两种燃料燃烧状况基本相同,且随着沿 y 轴自下往上扫描,温度逐渐升高;(2)发动机燃烧室内,氢气燃烧时的温度比乙烯燃烧时的温度要高和稳定;氢气燃烧过程温度基本处于2100K 左右,乙烯从点火至燃烧结束温度从2000K 左右逐渐降至1250K 左右。TDLAS 技术在复杂燃烧环境下的工程应用表明该技术具有抗干扰能力强、数据处理速度快的优点,可用于研制发动机燃烧场温度在线监测传感器。