激波风洞边界层转捩测量技术及应用

doi:10.7527/S1000-6893.2019.22740

Abstract

Abstract: Hypersonic boundary layer transition has an important influence on friction drag and heat transfer. The development of hypersonic vehicles is expected to accurately predict and control boundary layer transition. As the main ground equipment for hypersonic aerodynamic thermal environment test, the shock tunnel is an important equipment for studying hypersonic boundary layer transition. However, the original measurement technology of the tunnel is designed for engineering experiments, and it needs to be adapted and upgraded according to the characteristics of hypersonic boundary layer transition in shock tunnel. Therefore, according to the changes in physical parameters such as heat flux pressure density during the hypersonic boundary layer transition process, we develop the thin film heat flux sensor technique, the temperature-sensitive paint technique, the high frequency fluctuation pressure measurement, and the high definition schlieren visualization technique. The boundary layer transition experiment is carried out in China Aerodynamics Research and Development Center Ø2 m shock tunnel (FD-14A). The model is a 7° half-angle cone model with 0.05 mm nosetip bluntness, 10 nominal Mach number, the unit Reynolds number of 1.2×10⁷/m. Simultaneous measurements are carried out by using all the above techniques, obtaining good experimental results of boundary layer transition condition, fluctuation pressure spectrum characteristics, clear schlieren photos of the second mode wave and turbulent spots. The results obtained by these different measurement techniques can cross reference each other, and the theoretical analyses of linear stability are consistent with the experimental results.

Key words: shock tunnel, hypersonic boundary layer, transition measurement technology, high frequency fluctuation pressure, high definition schlieren visualization, second mode wave, turbulent spots

CLC Number:

V211

LI Qiang, JIANG Tao, CHEN Suyu, CHANG Yu, ZHAO Lei, ZHANG Kouli. Measurement technique and application of boundary layer transition in shock tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(8): 122740-122740.

References 32

[1]	SCHNEIDER S P. Flight data for boundary-layer transition at hypersonic and supersonic speeds[J]. Journal of Spacecraft Rockets, 1999, 36(1):8-20.
[22]	GROSSIR G, PINNA F, BONUCCI G, et al. Hypersonic boundary layer transition on a 7 degree half-angle cone at Mach 10[C]//The 7th AIAA Theoretical Fluid Mechanics Conference. Reston, VA:AIAA, 2014.
[2]	BERRY S A, HORVATH T J, HOLLIS B R, et al. X-33 hypersonic boundary layer transition:AIAA-1999-3560[R]. Reston, VA:AIAA, 1999.
[23]	LAURENCE S J, WAGNER A, OZAWA H, et al. Visualization of a hypersonic boundary-layer transition on a slender[C]//The 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA:AIAA, 2014.
[3]	MALIK M, ZANG T, BUSHNELL D. Boundary layer transition in hypersonic flows:AIAA-1990-5232[R]. Reston, VA:AIAA, 1999.
[24]	FUJⅡ K. An experiment of two dimensional roughness effect on hypersonic boundary-layer transition[C]//The 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA:AIAA, 2005.
[4]	LIN T C, GRABOWSKY W R, YELMGREN K E. The search for optimum configurations for reentry vehicles[J]. Journal of Spacecraft and Rockets, 1984, 21(2):142-149.
[25]	MARINEAU E C, MORARU C G, LEWIS D R, et al. Mach 10 boundary-layer transition experiments on sharp and blunted cones[C]//The 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA:AIAA, 2014.
[5]	WHITEHEAD A. NASP aerodynamics:AIAA-1989-5013[R]. Reston, VA:AIAA, 1989.
[26]	WADHAMS T P, MACLEAN M G, HOLDEN M S. Continuing experimental studies of high speed boundary layer transition in LENS facilities to further the development of predictive tools for boundary layer transition in flight[C]//The 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA:AIAA, 2013.
[6]	ERICSSON L E. Effect of boundary layer transition on vehicle dynamics:AIAA-1969-0106[R]. Reston, VA:AIAA, 1969.
[27]	TANNO H, KOMURO T, SATO K, et al. Measurement of surface pressure fluctuation in hypersonic high-enthalpy boundary layer on a 7-degree cone model[C]//The 41st AIAA Fluid Dynamics Conference and Exhibit. Reston, VA:AIAA, 2011.
[7]	MARTELLUCI A, NEFF R S. The influence of asymmetric transition on reentry vehicle motion:AIAA-1970-0987[R]. Reston, VA:AIAA, 1970.
[28]	BERRIDGE D C. Measurements of second-mode instability waves in hypersonic boundary layers with a high-frequency pressure transducer[D]. West Lafayette, IN:Purdue University, 2010.
[8]	HOLDEN M S. Studies of the effects of transitional and turbulent boundary layers on the aerodynamic performance of hypersonic reentry vehicles in high Reynolds number flows:Calspan Report AB-5834-A-2[R]. 1978.
[9]	罗纪生. 高超声速边界层的转捩及预测[J]. 航空学报, 2015, 36(1):357-372. LUO J S. Transition and prediction for hypersonic boundary layer[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):357-372(in Chinese).
[10]	ZHAO L, YU G T, LUO J S. Extension of eN method to general three-dimensional boundary layers[J]. Applied Mathematics and Mechanics (English Edition), 2017, 38(7):1007-1018.
[11]	陈坚强, 涂国华,张毅锋,等. 高超声速边界层转捩研究现状与发展趋势[J]. 空气动力学学报, 2017, 35(3):311-337. CHEN J Q, TU G H, ZHANG Y F, et al. Hypersonic boundary layer transition:What we know, where shall we go[J]. Acta Aerodynamica Sinica, 2017, 35(3):311-337(in Chinese).
[12]	国义军, 周宇,肖涵山,等. 飞行试验热流辨识和边界层转捩滞后现象[J]. 航空学报, 2017, 38(10):121255. GUO Y J, ZHOU Y, XIAO H S, et al. Delay phenomenon of boundary layer transition according to heating flux identified from flight test[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(10):121255(in Chinese).
[13]	杨武兵, 沈清,朱德华,等. 高超声速边界层转捩研究现状与趋势[J]. 空气动力学学报, 2018, 36(2):183-195. YANG W B, SHEN Q, ZHU D H, et al. Tendency and current status of hypersonic boundary layer transition[J]. Acta Aerodynamica Sinica, 2018, 36(2):183-195(in Chinese).
[29]	CASPER K M, BERESH S J, HENFLING J F, et al. High-speed schlieren imaging of disturbances in a transitional hypersonic boundary layer[C]//The 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA:AIAA, 2013.
[14]	RUFER S, BERRIDGE D C. Pressure fluctuation measurements in the NASA Langly 20-inch Mach 6 wind tunnel:AIAA-2012-3262[R]. Reston, VA:AIAA, 2012.
[30]	GROSSIR G, MASUTTI D, CHAZOT O. Flow characterization and boundary layer transition studies in VKI hypersonic facilities[C]//The 53rd AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2015.
[15]	BOUNITCH A, LEWIS D A, LAFFERTY J F. Improved measurements of "tunnel noise" pressure fluctuations in the AEDC hypervelocity wind tunnel No.9:AIAA-2011-1200[R]. Reston, VA:AIAA, 2011.
[31]	CASPER K M, BERESH S J, HENFLING J F, et al. Hypersonic wind-tunnel measurements of boundary-layer transition on a slender cone[J]. AIAA Journal, 2016, 54(4):1250-1263.
[32]	陈苏宇, 常雨,李强,等. 高超声速圆锥边界层转捩纹影显示[J]. 实验流体力学, 2019, 33(2):51-56. CHEN S Y, CHANG Y, LI Q, et al. Schlieren visualization of hypersonic boundary layer transition on a circular cone[J]. Journal of Experiments in Fluid Mechanics, 2019,33(2):51-56(in Chinese).
[16]	LAFFERTY J F, NORRIS J D. Measurements of fluctuating pitot pressure "tunnel noise" in the AEDC hypervelocity wind tunnel No.9:AIAA-2007-1678[R]. Reston, VA:AIAA, 2007.
[17]	张扣立, 常雨,孔荣宗,等. 温敏漆技术及其在边界层转捩测量中的应用[J]. 宇航学报, 2013, 34(6):860-865. ZHANG K L, CHANG Y, KONG R Z, et al. Temperature sensitive paint technique and its application in measurement of boundary layer transition[J]. Journal of Astronautics, 2013, 34(6):860-865(in Chinese).
[18]	李强, 张扣立,庄宇,等. 激波风洞边界层强制转捩试验研究[J]. 宇航学报, 2017, 38(7):758-765. LI Q, ZHANG K L, ZHUANG Y, et al. Experimental investigation on forced boundary-layer transition in shock tunnel[J]. Journal of Astronautics, 2017, 38(7):758-765(in Chinese).
[19]	周嘉穗, 张扣立,江涛,等. 激波风洞温敏热图技术初步试验研究[J]. 实验流体力学, 2013, 27(5):79-82. ZHOU J S, ZHANG K L, JIANG T, et al. Preliminary experimental study on temperature sensitive thermography used in shock tunnel[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(5):79-82(in Chinese).
[20]	张扣立, 周嘉穗,孔荣宗,等. CARDC激波风洞TSP技术研究进展[J]. 空气动力学学报, 2016, 34(6):738-743. ZHANG K L, ZHOU J S, KONG R Z, et al. Development of TSP technique in shock tunnel of CARDC[J]. Acta Aerodynamica Sinica, 2016, 34(6):738-743(in Chinese).
[21]	MACK L. Linear stability theory and the problem of supersonic boundary-layer transition[J]. AIAA Journal, 1975, 13(3):278-289.
[22]	GROSSIR G, PINNA F, BONUCCI G, et al. Hypersonic boundary layer transition on a 7 degree half-angle cone at Mach 10[C]//The 7th AIAA Theoretical Fluid Mechanics Conference. Reston, VA:AIAA, 2014.
[23]	LAURENCE S J, WAGNER A, OZAWA H, et al. Visualization of a hypersonic boundary-layer transition on a slender[C]//The 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA:AIAA, 2014.
[24]	FUJⅡ K. An experiment of two dimensional roughness effect on hypersonic boundary-layer transition[C]//The 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA:AIAA, 2005.
[25]	MARINEAU E C, MORARU C G, LEWIS D R, et al. Mach 10 boundary-layer transition experiments on sharp and blunted cones[C]//The 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA:AIAA, 2014.
[26]	WADHAMS T P, MACLEAN M G, HOLDEN M S. Continuing experimental studies of high speed boundary layer transition in LENS facilities to further the development of predictive tools for boundary layer transition in flight[C]//The 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA:AIAA, 2013.
[27]	TANNO H, KOMURO T, SATO K, et al. Measurement of surface pressure fluctuation in hypersonic high-enthalpy boundary layer on a 7-degree cone model[C]//The 41st AIAA Fluid Dynamics Conference and Exhibit. Reston, VA:AIAA, 2011.
[28]	BERRIDGE D C. Measurements of second-mode instability waves in hypersonic boundary layers with a high-frequency pressure transducer[D]. West Lafayette, IN:Purdue University, 2010.
[29]	CASPER K M, BERESH S J, HENFLING J F, et al. High-speed schlieren imaging of disturbances in a transitional hypersonic boundary layer[C]//The 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, VA:AIAA, 2013.
[30]	GROSSIR G, MASUTTI D, CHAZOT O. Flow characterization and boundary layer transition studies in VKI hypersonic facilities[C]//The 53rd AIAA Aerospace Sciences Meeting. Reston, VA:AIAA, 2015.
[31]	CASPER K M, BERESH S J, HENFLING J F, et al. Hypersonic wind-tunnel measurements of boundary-layer transition on a slender cone[J]. AIAA Journal, 2016, 54(4):1250-1263.
[32]	陈苏宇, 常雨,李强,等. 高超声速圆锥边界层转捩纹影显示[J]. 实验流体力学, 2019, 33(2):51-56. CHEN S Y, CHANG Y, LI Q, et al. Schlieren visualization of hypersonic boundary layer transition on a circular cone[J]. Journal of Experiments in Fluid Mechanics, 2019,33(2):51-56(in Chinese).

Measurement technique and application of boundary layer transition in shock tunnel

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