高超声速平板边界层中波纹粗糙壁峰值热流的变化规律及预测

doi:10.7527/S1000-6893.2022.27769

Abstract

Abstract:

Micro ablation on the surface of new-type vehicles will lead to increased local heat flux on the wall surface. This study uses corrugated roughness with roughness height smaller than 600 μm to simulate micro ablative surfaces， and calculates the variation law of the peak heat flux on the wall surface with uniform corrugated roughness by directly solving the Navier-Stokes equation. It is found that the surface peak heat flux caused by roughness is inversely proportional to the 0.5 times of the flow position， the surface peak heat flux is proportional to the roughness height and decreases with increasing width， and is more influenced by the height than the width. Meanwhile， the influence results of the Mach number and wall temperature on the surface peak heat flux at the wall show that the relative surface peak heat flux increment is inversely proportional to both the Mach number and wall temperature. Further， based on the smooth flat plate heat flux theory solution， we provide the surface peak heat flux prediction formula. Detailed verification of the working conditions reveals that the formula can accurately predict the surface peak heat flux in the range of Mach number 4-10 and wall temperature 300-800 K with an error of no more than 8%. For other wall forms， such as elliptical and dispersive sine types， the formula can also produce an accurate prediction.

Key words: hypersonic, rough wall, aerodynamic heat, predictive model, peak heat flux

CLC Number:

V211.3

Xiangzhi KONG, Yufeng HAN. Patterns and prediction of surface peak heat flux in hypersonic flat plate boundary layer over wave wall[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127769-127769.

Figures/Tables 31

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References 28

1	COLEBROOK C F， WHITE C M. Experiments with fluid friction in roughened pipes ［J］. Proceedings of the Royal Society of London Series A-Mathematical and Physical Sciences， 1937， 161（906）： 367-381.
2	SCHLICHTING H. Experimentelle untersuchungen zum rauhigkeitsproblem ［J］. Ingenieur-Archiv， 1936， 7（1）： 1-34.
3	NIKURADSE J. Laws of flow in rough pipes： Technical Memorandum 1292［R］. Washington： NACA， 1950.
4	SIGAL A， DANBERG J E. New correlation of rough-ness density effect on the turbulent boundary layer ［J］. AIAA Journal， 1990， 28（3）： 554-556.
5	NAPOLI E， ARMENIO V， DE MARCHIS M. The effect of the slope of irregularly distributed roughness elements on turbulent wall-bounded flows ［J］. Journal of Fluid Mechanics， 2008， 613： 385-94.73.
6	安复兴，李磊，苏伟，等. 高超声速飞行器气动设计中的若干关键问题［J］. 中国科学（物理学力学天文学）， 2021， 51（10）： 2-21
	AN F X， LI L， SU W， LIU W L， DONG C. Several key issues in the aerodynamic design of hypersonic vehicles ［J］. Science in China： Physics Mechanics Astronomy， 2021， 51（10）： 2-21 （in Chinese）.
7	BERTRAM M， WEINSTEIN L， CARY JR A， et al. Heat transfer to wavy wall in hypersonic flow ［J］. AIAA Journal， 1967， 5（10）： 1760-1767.
8	JAECK C L. Analysis of pressure and heat transfer tests on surface roughness elements with laminar and turbulent boundary layers ［M］. Washington D.C.： National Aeronautics and Space Administration， 1966.
9	ABBETT M J， ANDERSON A D， COOPER L， et al. Passive Nosetip Technology （PANT） Program. Volume 20. Investigation of flow phenomena over reentry vehicle nosetips［R］. 1975.
10	DIRLING， JR R， SWAIN C， STOKES T. The effect of transition and boundary layer development on hypersonic reentry shape change［C］∥10th Thermophysics Conference. 1975： 673.
11	PHINNEY R E. Mechanism for heat-transfer to a rough blunt body ［J］. Letters in Heat and Mass Transfer， 1974， 1（2）： 181-186.
12	GRABOW R， WHITE C. Surface roughness effects nosetip ablation characteristics ［J］. AIAA Journal， 1975， 13（5）： 605-609.
13	NESTLER D. Compressible turbulent boundary-layer heat transfer to rough surfaces ［J］. AIAA Journal， 1971， 9（9）： 1799-1803.
14	SEIDMAN M. Rough wall heat transfer in a compressible turbulent boundary layer［C］∥16th Aerospace Sciences Meeting. 1978： 163.
15	NESTLER D. The effects of surface discontinuities on convective hear transfer in hypersonic flow［C］∥20th Thermophysics Conference. 1985： 971.
16	POLAK A， WERLE M， VATSA V， et al. Numerical study of separated laminar boundary layers over multiple sine-wave protuberances ［J］. Journal of Spacecraft and Rockets， 1976， 13（3）： 168-173.
17	NOVIKOV A， EGOROV I， FEDOROV A. Direct numerical simulation of supersonic boundary layer stabilization using grooved wavy surface［C］∥48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. 2010： 1245.
18	李俊红，张亮，俞继军，等. 高超声速可压缩流中粗糙壁热流研究［J］. 计算物理， 2017， 34（2）： 165-174.
	LI J H， ZHANG L， YU J J， et al. Study on rough wall heat flow in hypersonic compressible flow ［J］. Computational Physics， 2017， 34（2）： 165-174 （in Chinese）.
19	李玉川，鲍麟. 波状粗糙壁模型流动的壁面热流和阻力关联关系的数值研究［J］.中国科学院大学学报，2019，36（6）：736-744.
	LI Y C， BAO L. Numerical study on the relationship between wall heat flow and resistance in wavy rough wall model flow［J］. Journal of University of Chinese Academy of Sciences，2019，36（06）：736-744 （in Chinese）.
20	KUMAR C， REDDY K. Hypersonic interference heating on flat plate with short three-dimensional protuberances ［J］. AIAA Journal， 2014， 52（4）： 747-756.
21	ESTRUCH-SAMPER D. Reattachment heating up-stream of short compression ramps in hypersonic flow ［J］. Experiments in Fluids， 2016， 57（5）： 1-17.
22	AVALLONE F， RAGNI D， SCHRIJER F F， et al. Study of a supercritical roughness element in a hypersonic laminar boundary layer ［J］. AIAA Journal， 2016， 54（6）： 1892-1900.
23	THAKKAR M， BUSSE A， SANDHAM N. Surface correlations of hydrodynamic drag for transitionally rough engineering surfaces ［J］. Journal of Turbulence， 2017， 18（2）： 138-169.
24	MATHAUSER E E. Research， design considerations， and technological problems of structures for winged aerospace vehicles ［J］. NASA Special Publication， 1962， 28： 13.
25	ZHAO L， DONG M， YANG Y. Harmonic linearized Navier-Stokes equation on describing the effect of surface roughness on hypersonic boundary-layer transition［J］. Physics of Fluids， 2019， 31（3）： 034108.
26	程晓丽，艾邦成，王强. 基于分子平均自由程的热流计算壁面网格准则［J］. 力学学报，2010，42（06）：1083-1089.
	CHENG X L， AI B C， WANG Q. Wall mesh criterion for heat flow calculation based on molecular mean free path［J］. Acta Mechanica Sinica， 2010，42（6）：1083-1089 （in Chinese）.
27	马崇立，刘景源. 网格对高超声速钝头体表面热流数值模拟结果的影响［J］. 航空学报， 2023， 44（5）： 126710.
	MA C L， LIU J Y. Effect of Grid Strategy on Numerical Simulation Results of Aerothermal Heating Loads over Hypersonic Blunt Bodies［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（5）： 126710 （in Chinese）.
28	ANDERSON J D. Hypersonic and high temperature gas dynamics［M］. Reston： AIAA， 2000： 243-247.

粗糙高度h/mm	粗糙宽度w/mm
0.070 2	1.755
0.140 4	3.51
0.210 6	5.265
0.280 8	7.02
0.421 2	10.53

马赫数	壁面温度/K	粗糙高度/mm	粗糙宽度/mm
5.0	600	0.210 6	10.53
7.0	700	0.526 5	10.53
8.0	800	0.379 08	10.53

马赫数	壁面温度/K	粗糙高度/mm	粗糙宽度/mm
4.0	350	0.210 6	10.53
4.0	800	0.210 6	10.53
10.0	350	0.210 6	10.53
10.0	800	0.210 6	10.53

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Patterns and prediction of surface peak heat flux in hypersonic flat plate boundary layer over wave wall

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