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Modelling and shock control for a V-shaped blunt leading edge

Published online by Cambridge University Press:  01 August 2023

Dake Kang Open the ORCID record for Dake Kang [Opens in a new window] ,
Chao Yan Open the ORCID record for Chao Yan [Opens in a new window] ,
Sijia Liu Open the ORCID record for Sijia Liu [Opens in a new window] ,
Zhaowei Wang  and
Zhenhua Jiang Open the ORCID record for Zhenhua Jiang [Opens in a new window]
Dake Kang
Affiliation:
National Key Laboratory of Computational Fluid Dynamics, Beihang University, Beijing 100191, PR China
Chao Yan
Affiliation:
National Key Laboratory of Computational Fluid Dynamics, Beihang University, Beijing 100191, PR China
Sijia Liu
Affiliation:
National Key Laboratory of Computational Fluid Dynamics, Beihang University, Beijing 100191, PR China
Zhaowei Wang
Affiliation:
China Academy of Launch Vehicle Technology, Beijing 100076, PR China
Zhenhua Jiang*
Affiliation:
National Key Laboratory of Computational Fluid Dynamics, Beihang University, Beijing 100191, PR China
*
† Email address for correspondence: jiangzhenhua@buaa.edu.cn
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Abstract

Hypersonic flow on a V-shaped blunt leading edge (VSBLE) at Mach 12 is numerically investigated. A series of self-induced shock–shock interactions and shock wave/boundary layer interactions (SWBLIs) cause extremely high heat flux peaks on the crotch of the VSBLE. Based on these shock structures, a simplified model that divides the flow field into inviscid and viscous areas is constructed. This model can quickly solve the shock interactions and predict the heating/pressure peaks with high accuracy. Furthermore, a shock control bump (SCB) is placed on the SWBLI region to split the strong incident shock into a weaker multi-wave system. The mechanism study of the SCB shows that the inviscid effect significantly reduces the heating/pressure peaks, and the viscous effect suppresses the SWBLI-induced separation. Finally, a VSBLE with SCBs is numerically investigated. The heat flux peak is reduced by 66 % compared to that without the SCBs. The robustness of the SCB under various working conditions is also evaluated. This paper provides an idea for the simplified solution of complex shock interactions and extends the application of the SCB as a thermal protection device in hypersonic flow for the first time.

JFM classification

Compressible Flows: Hypersonic Flow Compressible Flows: Shock waves
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 968 , 10 August 2023 , A15
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Copyright
© The Author(s), 2023. Published by Cambridge University Press

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References

Ashill, P.R., Fulker, J.L. & Hackett, K.C. 2005 A review of recent developments in flow control. Aeronaut. J. 109 (1095), 205–232.CrossRefGoogle Scholar
Birkemeyer, J., Rosemann, H. & Stanewsky, E. 2000 Shock control on a swept wing. Aerosp. Sci. Technol. 4 (3), 147–156.CrossRefGoogle Scholar
Boldyrev, S.M., Borovoy, V.Y., Chinilov, A.Y., Gusev, V.N., Krutiy, S.N., Struminskaya, I.V., Yakovleva, L.V., Délery, J. & Chanetz, B. 2001 A thorough experimental investigation of shock/shock interferences in high Mach number flows. Aerosp. Sci. Technol. 5 (3), 167–178.CrossRefGoogle Scholar
Brown, J.L. 2013 Hypersonic shock wave impingement on turbulent boundary layers: computational analysis and uncertainty. J. Spacecr. Rockets 50 (1), 96–123.CrossRefGoogle Scholar
Bruce, P.J.K. & Colliss, S.P. 2015 Review of research into shock control bumps. Shock Waves 25 (5), 451–471.CrossRefGoogle Scholar
Chew, Y.T. 1979 Shockwave and boundary layer interaction in the presence of an expansion corner. Aeronaut. Q. 30 (3), 506–527.CrossRefGoogle Scholar
Edney, B. 1968 Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. FFA Rep. No. 115. Aeronautical Research Institute of Sweden.CrossRefGoogle Scholar
Fay, J.A. & Riddell, F.R. 1958 Theory of stagnation point heat transfer in dissociated air. J. Aerosp. Sci. 25 (2), 73–85.CrossRefGoogle Scholar
Giepman, R.H.M., Schrijer, F.F.J. & van Oudheusden, B.W. 2014 Flow control of an oblique shock wave reflection with micro-ramp vortex generators: effects of location and size. Phys. Fluids 26 (6), 66101.CrossRefGoogle Scholar
Grasso, F., Purpura, C., Chanetz, B. & Délery, J. 2003 Type III and type IV shock/shock interferences: theoretical and experimental aspects. Aerosp. Sci. Technol. 7 (2), 93–106.CrossRefGoogle Scholar
Hains, F.D. & Keyes, J.W. 1972 Shock interference bell aerospace, heating in hypersonic flows. AIAA J. 10 (11), 1441–1447.CrossRefGoogle Scholar
Jiang, Z. & Yan, C. 2019 On the use of thermally perfect gas model for heating prediction of laminar and turbulent SWBLI. Aerosp. Sci. Technol. 95, 105484.CrossRefGoogle Scholar
Jiang, Z.-H., Yan, C., Yu, J. & Gao, B. 2017 Effective technique to improve shock anomalies and heating prediction for hypersonic flows. AIAA J. 55 (4), 1475–1479.CrossRefGoogle Scholar
Launder, B.E. & Spalding, D.B. 1974 The numerical computation of turbulent flows. Comput. Meth. Appl. Mech. Engng 3 (2), 269–289.CrossRefGoogle Scholar
Li, S., Yan, C., Kang, D., Liu, S. & Jiang, Z. 2023 Investigation of flow control methods for reducing heat flux on a V-shaped blunt leading edge under real gas effects. Phys. Fluids 35 (3), 36113.CrossRefGoogle Scholar
Li, Z. & Yang, J. 2015 Leading edge bluntness effects on shock wave/boundary layer interactions near a convex corner. In 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Reston, Virginia, p. 07062015. American Institute of Aeronautics and Astronautics.CrossRefGoogle Scholar
Li, Z., Zhang, Z., Wang, J. & Yang, J. 2019 Pressure–heat flux correlations for shock interactions on V-shaped blunt leading edges. AIAA J. 57 (10), 4588–4592.CrossRefGoogle Scholar
Liu, S., Kang, D., Yan, C., Sun, M. & Jiang, Z. 2022 Passive flow control for heat flux reduction on V-shaped blunt leading edges. In 2022 13th International Conference on Mechanical and Aerospace Engineering (ICMAE), p. 108. IEEE.CrossRefGoogle Scholar
Malo-Molina, F.J., Gaitonde, D.V., Ebrahimi, H.B. & Ruffin, S.M. 2010 Three-dimensional analysis of a supersonic combustor coupled to innovative inward-turning inlets. AIAA J. 48 (3), 572–582.CrossRefGoogle Scholar
Markarian, C.F. 1968 Heat transfer in shock wave boundary layer interaction regions. Tech. Rep. 4485. Naval Weapons Center NWC.Google Scholar
Menter, F.R. 1994 Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J. 32 (8), 1598–1605.CrossRefGoogle Scholar
Pasquariello, V., Hickel, S. & Adams, N.A. 2017 Unsteady effects of strong shock-wave/boundary-layer interaction at high Reynolds number. J. Fluid Mech. 823, 617–657.CrossRefGoogle Scholar
Pirozzoli, S. & Grasso, F. 2006 Direct numerical simulation of impinging shock wave/turbulent boundary layer interaction at M=2.25. Phys. Fluids 18 (6), 65113.CrossRefGoogle Scholar
Qin, N., Wong, W.S. & Le Moigne, A. 2008 Three-dimensional contour bumps for transonic wing drag reduction. Proc. Inst. Mech. Engrs G: J. Aerosp. Engng 222 (5), 619–629.CrossRefGoogle Scholar
Reubush, D., Nguyen, L. & Rausch, V. 2004 Review of X-43A return to flight activities and current status. In 12th AIAA International Space Planes and Hypersonic Systems and Technologies, Reston, Virigina. American Institute of Aeronautics and Astronautics.CrossRefGoogle Scholar
Roe, P. 1981 Approximate Riemann solvers, parameter vectors, and difference schemes. J. Comput. Phys. 43 (2), 357–372.CrossRefGoogle Scholar
Sathia Narayanan, A. & Verma, S. 2015 Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion corner. In 53rd AIAA Aerospace Sciences Meeting, Reston, Virginia. American Institute of Aeronautics and Astronautics.CrossRefGoogle Scholar
Schülein, E., Schnepf, C. & Weiss, S. 2022 Concave bump for impinging-shock control in supersonic flows. AIAA J. 60 (5), 2749–2766.CrossRefGoogle Scholar
Sriram, R., Srinath, L., Devaraj, M.K.K. & Jagadeesh, G. 2016 On the length scales of hypersonic shock-induced large separation bubbles near leading edges. J. Fluid Mech. 806, 304–355.CrossRefGoogle Scholar
Wang, D., Li, Z., Zhang, Z., Liu, N.-S., Yang, J. & Lu, X.-Y. 2018 Unsteady shock interactions on V-shaped blunt leading edges. Phys. Fluids 30 (11), 116104.CrossRefGoogle Scholar
White, M.E. & Ault, D.A. 1996 Expansion corner effects on hypersonic shock wave/turbulent boundary-layer interactions. J. Propul. Power 12 (6), 1169–1173.CrossRefGoogle Scholar
Wieting, A.R. & Holden, M.S. 1989 Experimental shock-wave interference heating on a cylinder at Mach 6and 8. AIAA J. 27 (11), 1557–1565.CrossRefGoogle Scholar
Xiao, F., Li, Z., Zhang, Z., Zhu, Y. & Yang, J. 2018 Hypersonic shock wave interactions on a V-shaped blunt leading edge. AIAA J. 56 (1), 356–367.CrossRefGoogle Scholar
Yao, Y., Li, S.G. & Wu, Z.N. 2013 Shock reflection in the presence of an upstream expansion wave and a downstream shock wave. J. Fluid Mech. 735, 61–90.CrossRefGoogle Scholar
Zhang, Z., Li, Z., Huang, R. & Yang, J. 2019 a Experimental investigation of shock oscillations on V-shaped blunt leading edges. Phys. Fluids 31 (2), 26110.CrossRefGoogle Scholar
Zhang, Z., Li, Z. & Yang, J. 2021 a Transitions of shock interactions on V-shaped blunt leading edges. J. Fluid Mech. 912, A12.CrossRefGoogle Scholar
Zhang, Y., Tan, H.-J., Li, J.-F. & Yin, N. 2019 b Control of cowl-shock/boundary-layer interactions by deformable shape-memory alloy bump. AIAA J. 57 (2), 696–705.CrossRefGoogle Scholar
Zhang, Z., Tong, F., Duan, J. & Li, X. 2021 b Direct numerical simulation of supersonic turbulent expansion corner with shock impingement. Phys. Fluids 33 (10), 105104.CrossRefGoogle Scholar
Zhang, Z., Yan, C., Kang, D.-K. & Jiang, Z.-H. 2022 Numerical study of reverse jet for mitigating shock/shock interaction heating. Aerosp. Sci. Technol. 131, 108015.CrossRefGoogle Scholar
Zhou, T., Liu, Z., Lu, Y., Kang, D. & Yan, C. 2022 Control of oblique breakdown in a supersonic boundary layer employing a local cooling strip. J. Fluid Mech. 949, A4.CrossRefGoogle Scholar
Zhong, X. 1994 Application of essentially nonoscillatory schemes to unsteady hypersonic shock-shock interference heating problems. AIAA J. 32 (8), 1606–1616.CrossRefGoogle Scholar
Zukoski, E.E. 1967 Turbulent boundary-layer separation in front of a forward-facing step. AIAA J. 5 (10), 1746–1753.CrossRefGoogle Scholar