Flow structure of incident shock wave boundary layer interaction with separation

YAO Yao; GAO Bo

doi:10.7638/kqdlxxb-2018.0155

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Flow structure of incident shock wave boundary layer interaction with separation

更新时间：2026-05-28

- Flow structure of incident shock wave boundary layer interaction with separation
- Vol. 37, Issue 5, Pages: 740-747, 769(2019)
- 作者机构：
  
  北京宇航系统工程研究所,北京,100073
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0155
  CLC： V211.3
- Published：2019
- 稿件说明：
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姚瑶, 高波. 入射激波边界层干扰分离流场结构研究[J]. 空气动力学学报, 2019, 37(5): 740-747, 769.

YAO Yao, GAO Bo. Flow structure of incident shock wave boundary layer interaction with separation[J]. 2019, 37(5): 740-747, 769.
姚瑶, 高波. 入射激波边界层干扰分离流场结构研究[J]. 空气动力学学报, 2019, 37(5): 740-747, 769. DOI： 10.7638/kqdlxxb-2018.0155.

YAO Yao, GAO Bo. Flow structure of incident shock wave boundary layer interaction with separation[J]. 2019, 37(5): 740-747, 769. DOI： 10.7638/kqdlxxb-2018.0155.

摘要

入射激波边界层干扰易导致边界层分离，为了分析其局部流场结构，捕获局部高压、高热区，掌握分离泡的大小，本文针对入射激波导致的边界层分离流场，构造简化模型，辅助以极曲线理论分析描述，结合自由干扰理论、激波关系式以及分离区长度工程估算首次给出完整的理论求解。该理论模型可快速获得流动图画，给出流场参数分布，便于分析整体流场结构，并得到了很好的数值验证。运用该理论模型对分离泡高度进行了参数化分析，分离泡高度随来流马赫数的增大先略有减小再增大，同时是外压缩角以及飞行高度的增函数。

Abstract

Shock wave boundary layer interaction prefers to induce boundary layer separation

and it's necessary to analyze the flow structure

local high pressures and heat flux

and the separation bubble size. In this paper

we propose an analytical model for this typical flow structure

and the polar theory is used for auxiliary analysis. Based on the FIT

classical shock relationship

and fitting formula of separation length

the analytical model can be solved. With the analytical model

we can quickly gain the flow structure and parameters which compares well with numerical simulation. Also

we use this model to analyze the height of separation bubble. The height increases with increasing flight altitude and deflection angle for incident shock wave

and it first decreases slightly then increases as incoming Mach number increases.

关键词

Keywords

references

FERRI A. Experimental results with airfoils tested in the high-speed tunnel at guidonia[R]. National Advisory Commitee for Aeronautics, 1940.

FAGE A, SARGENTR F. Shock wave and boundary layer phenomena near a flat surface[C]//Proceedings of the Royal Society of London, Series A: Mathematical and Physical Sciences, 1947, 190(1020): 1-20.

BARRY F W, SHAPIRO A H, NEUMANN E P. The interaction of shock waves with boundary layers on a flat surface[J]. Journal of Aerospace Sciences, 1951, 18(4):229-238.

LIEPMANN H W, ROSHKO A, DHAWANS. On reflection of shock waves from boundary layers[R]. NACA Rept. 1100, 1952.

JOHANNESEN N H. Experiments on two-dimensional supersonic flow in corners and over concave surfaces[J]. The London, Edinburgh, and Dublin Philosophical Magazine and Journal of Science, 1952, 43(340):568-580.

BABINSKY H, HARVEY J K. Shock wave boundary layer interactions[M]. Cambridge University Press, 2011.

GREEN J E. Interactions between shock waves and turbulent boundary layers[J]. Progress in Aerospace Sciences, 1970, 11:235-340.

MACCOMACK R W. Numerical solution of the interaction of a shock wave with a laminar boundary layer[J]. Lecture Notes in Physis. 1971:151-163.

BEAM R M, WARMING R F. An implicit factored scheme for the compressible Navier-Stokes equation[J]. AIAA J, 1978, 16(4):393-402.

BODONYI R J, SMITHF T. Shock wave laminar boundary layer interaction in supercritical transonic flow[J]. Computers Fluids, 1986, (2):92-108.

MALLINSON S G, GAI S L, MUDFORD N R. The interaction of a shock wave with a laminar boundary layer at a compressing corner in high-enthalpy flows including real gas effects[J]. Journal of Fluid Mechanics, 1997, 342:1-35.

PRINCE S A, Vannahme M, Stollery J L. Experiments on the hypersonic turbulent shock-wave/boundary-layer interaction and the effects of surface roughness[J]. The Aeronautical Journal, 2005, 109(1094):177-184.

GONG A L, LIU Z, YANG Y J, et al. Numerical study on hypersonic double cone separated flow[J]. Acta Aerodynamica Sinica, 2014, 32(06):767-771.(in Chinese)

ZHAO Y F. Study of shock wave/boundary layer interaction and boundary layer transition using high-order numerical scheme[D]. Changsha: National University of Defense Technology, 2015. (in Chinese)

TONG F L, LI X L, TANG Z G, et al. Transition effect on separation bubble of shock wave/boundary layer interactions in a compression ramp[J]. Acta Aeronautica et AstronauticaSinica, 2016, 37(10):2909-2921. (in Chinese)

DONG X R, CHEN Y H, DONG G, et al. DES numerical study of shock wave/boundary layer interactions in hypersonic flows controlled by double micro-ramps[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(6):1771-1780. (in Chinese)

SONG Y F, XU J L, ZHANG Y, et al. Research of compressible turbulence model in shock wave/boundary-layer interaction flow at a compression corner[J]. Journal of Propulsion Technology, 2017, 38(2):281-288. (in Chinese)

CHEN X L, GUO W, QIN X G, et al. Hypersonic shock wave boundary layer interaction and fluctuation pressure research[C]//The 3rd China aeronautical science and technology conference proceedings (part one): 141-146. (in Chinese)

WANG J, TAN H J, HUANG H X. Shock wave/boundary layer interactions induced by bump in the Bump inlet[J]. Journal of Aerospace Power, 2018, 31(1):91-107. (in Chinese)

KOTOV D V, YEE H C, WRAY A, et al. High order numerical methods for LES of turbulent flows with shocks[J]. Acta Aerodynamica Sinica, 2016, 34(2):190-203.

CHAPMAN D R, KUEHN D K, LARSON H K. Investigation of separated flows in supersonic and subsonic with emphasis on the effect of transition[R]. NACA Report, 1958.

BURGGRAFO R. Asymptotic theory of separation and reattachment of a laminar boundary layer on a compression ramp[R]. NASA STI/Recon Technical Report N, 1975, 76: 10435.

NEILAND V. Flow behind the boundary layer separation point in supersonic stream[J]. Fluid Dynamics, 1971, 6(3):378-384.

STEWARTSON K, WILLIAMS P. On self-induced separation Ⅱ[J]. Mathematika 1973, 20(1):98-108.

MILLER J H, TANNEHILLJ C, LAWRENCE S L. PNS algorithm for solving supersonic flows with upstream influences[J]. AIAA Journal, 1998, 38:1837-1845.

RAMESH M D, TANNEHILL J C. Correlations to predict the streamwise influence regions in supersonic turbulent flows[J]. Journal of Aircraft, 2004, 41(2):274-283.

KATZER E. On the lengthscales of laminar shock boundary layer interaction[J]. Journal of Fluid Mechanics, 1989, 206:477-496.

KRISHNAN L, YAO Y, SANDHAM N D, et al. On the response of shock-induced separation bubble to small amplitude disturbances[J]. Modern Physics Letters B, 2005, 19(28n29):1495-1498.

HENDERSON L F. The reflection of a shock wave at a rigid wall in the presence of a boundary layer[J]. Journal of Fluid Mechanics, 1967, 30(4):699-722.

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