Aerodynamic heating produced in the hypersonic flight test will destroy the pressure transducers mounted on the vehicle surface and lead to measurement failure. Recessed installation of transducers can avoid direct contact with the high temperature air surrounding the vehicles and abate the excessive heat loads. In this paper, experimental measurements of pressure fluctuations in a hypersonic boundary layer are carried out based on recessed installation of transducers and the effects of opening diameter on characteristics of fluctuating pressure are studied. The results show that the intensity of pressure fluctuation is reduced and the correlation of flow field is enhanced as the opening diameter increases. Recess mounting could cause cavity flow, and the influence of cavity flow on fluctuation pressure measurement is reduced as the opening diameter increases. Within the frequency band of 10-20 kHz, the opening diameter only mildly influences the fluctuating pressure intensity, but within the frequency band of 1-10 kHz, the opening diameter exerts more significant effects on the wave period of pressure fluctuations. Nonlinear phase lock resonance transfers the energy from high frequency structures to low frequency structures, leading to the flow structures occurring self-interaction and nonlinear phase coupling tending to the low frequency. As the opening diameter increases, the nonlinear phase coupling finally vanishes. In addition, the energy distributions of different scale structures share higher similarity with those under flush mounting with the increasing opening diameter.
YAO Shiyong
,
MIN Changwan
. Effects of opening diameter on measurement of recessed pressure transducers[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018
, 39(12)
: 122029
-122029
.
DOI: 10.7527/S1000-6893.2018.22029
[1] 李周复. 风洞特种试验技术[M]. 北京:航空工业出版社, 2010. LI Z F. Special test techniques for wind tunnel[M]. Beijing:Aviation Industry Press, 2010(in Chinese).
[2] 原正庭. 亚音速飞机压力分布测量[J]. 航空学报, 1998, 19(4):486-488. YUAN Z T. In-flight measurement of static pressure on a subsonic transport aircraft[J]. Acta Aeronautica et Astronautica Sinica, 1998, 19(4):468-488(in Chinese).
[3] 陈怦, 余俊雅, 张德元, 等. 三角翼飞机气动压力测量试飞技术研究[J]. 飞行力学, 2001, 19(3):56-59. CHEN P, YU J Y, ZHANG D Y, et al. Flight test research of aerodynamics pressure measurement technique for a delta-wing aircraft[J]. Flight Dynamics, 2001, 19(3):56-59(in Chinese).
[4] 曹虎成, 周占廷, 李少鹏. 运输机襟翼压力分布飞行试验测量[J]. 实验流体力学, 2010, 24(3):96-98. CAO H C, ZHOU Z T, LI S P. In-flight test measurement of flap pressure distribution for aerotransport[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(3):96-98(in Chinese).
[5] 褚江, 王晓江, 陈胜杰. 超音速下压力分布测量飞行试验研究[J]. 科学技术与工程, 2012, 12(12):2893-2896. CHU J, WANG X J, CHEN S J. In-flight investigation of pressure distribution measurement in the supersonic flow[J]. Science Technology and Engineering, 2012, 12(12):2893-2896(in Chinese).
[6] RAMAN K R. Surface pressure fluctuations in hypersonic turbulent boundary layers:AIAA-1973-0997[R]. Reston, VA:AIAA, 1973.
[7] JULIANO T J. Nozzle modification for high-Reynolds-number quiet flow in the Boeing/AFOSR Mach-6 quiet tunnel[D]. West Lafayette, IN:Purdue University, 2006.
[8] CASPER K M, Hypersonic wind-tunnel measurements of boundary-layer pressure fluctuations[D]. West Lafayette, IN:Purdue University, 2009.
[9] GILBERT P L. Effect of tunnel noise on laminar stagnation-point heating at Mach 6[D]. West Lafayette, IN:Purdue University, 2010.
[10] WHEATON B M. Roughness-induced instabilities in a Mach-6 laminar boundary layer[D]. West Lafayette, IN:Purdue University, 2012.
[11] MARINEAU E C, MORARU C G, LEWIS D R, et al. Mach 10 boundary-layer transition experiments on sharp and blunted cones:AIAA-2014-3108[R]. Reston, VA:AIAA, 2014.
[12] JULIANO T J, BORG M P, SCHNEIDER S P. Quiet tunnel measurements of HIFiRE-5 boundary-layer transition[J]. AIAA Journal, 2015, 53(4):832-846.
[13] BORG M P, KIMMEL R L, STANFIELD S. Traveling crossflow instability for the HIFiRE-5 elliptic cone[J]. Journal of Spacecraft and Rockets, 2015, 52(3):664-673.
[14] HANLY R D. Effects of transducer flushness on fluctuating surface pressure measurements:AIAA-1975-0534[R]. Reston, VA:AIAA, 1975.
[15] HOWE J R, LANGANELLI A L. Surface pressure fluctuation measurements in attached transitional turbulent boundary layers at supersonic and hypersonic speeds:AIAA-1977-0113[R]. Reston, VA:AIAA, 1977.
[16] BERRY S A, CHEN F J, WILDER M C, et al. Boundary layer transition experiments in support of the hypersonics program:AIAA-2007-4266[R]. Reston, VA:AIAA, 2007.
[17] HANNEMANN K, SCHRAMM J M, WAGNER A, et al. A closely coupled experimental and numerical approach for hypersonic and high enthalpy flow investigations utilising the HEG shock tunnel and the DLR TAU code:NATO TR RTO-EN-AVT-186[R]. 2010.
[18] WELCH P D. The use of fast Fourier transform for the estimation of power spectra:A method based on time averaging over short, modified periodograms[J]. IEEE Transactions on Audio and Electroacoust, 1967, 15(2):70-73.
[19] 韩健. 高超声速尖锥边界层流动稳定性的子波分析与互双谱分析[D]. 天津:天津大学, 2010. HAN J. Wavelet analysis and cross bispectrum analysis of flow instability for hypersonic sharp cone boundary layer[D]. Tianjin:Tianjin University, 2010(in Chinese).
[20] FARGE M. Wavelet transforms and their applications to turbulence[J]. Annual Review of Fluid Mechanics, 1992, 24:395-458.
CJA