Hostname: page-component-89b8bd64d-46n74 Total loading time: 0 Render date: 2026-05-08T06:30:52.349Z Has data issue: false hasContentIssue false
  • English
  • Français

Effects of wall cooling on hypersonic shock wave turbulent boundary layer interaction

Published online by Cambridge University Press:  24 July 2025

Z. Tang Open the ORCID record for Z. Tang [Opens in a new window] ,
H. Xu ,
X. Li  and
J. Ren
Z. Tang*
Affiliation:
Tsinghua University, Beijing, China
H. Xu
Affiliation:
Tsinghua University, Beijing, China
X. Li
Affiliation:
Tsinghua University, Beijing, China
J. Ren
Affiliation:
Tsinghua University, Beijing, China
*
Corresponding author: Zhenyuan Tang; Email: tangzy21@mails.tsinghua.edu.cn
Get access Rights & Permissions [Opens in a new window]

Abstract

Wall cooling is a promising method in controlling compressible flows, including hypersonic shock wave turbulent boundary layer interaction (STBLI). Based on the verified DNS method, a 30-degree compression ramp is used to generate STBLI for Ma of 5 and wall to recovery temperature ratio ranging from 0.2 to 1.0. The results indicate that the separation zone decreases for cold wall conditions and quantitatively validate the wall-temperature-corrected interaction scaling theory in recent literature. The heat transfer results show that the wall cooling greatly influences the heat flux distribution and peak values in STBLI. The two-stage heat flux increase disappears for the cold wall, which corresponds to the reduced separation bubble. The local decrease of the recovery temperature is observed after the shock, which causes the negative heat flux minimum for near ‘adiabatic’ wall conditions and can be attributed to the acceleration of the near-wall supersonic fluid in the turning process. On the whole, the decrease of the wall temperature leads to the 24.3% decrease of the peak heat flux enhancement, and the underlying mechanism is the decrease of the near-wall turbulent aerodynamic heat dissipation enhancement for the wall cooling.

Keywords

aerodynamic heatdirect numerical simulationhypersonicshock wave turbulent boundary layer interactionwall cooling

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 129 , Issue 1341 , November 2025 , pp. 3184 - 3201
Check for updates
Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

Dolling, D.S. Fifty years of shock wave boundary layer interaction research: what next?, AIAA J., 2001, 39, (8), pp 1517–1531.CrossRefGoogle Scholar
Delery, J.M. Shock wave/turbulent boundary layer interaction and its control, Prog. Aerosp. Sci., 1985, 22, (4), pp 209–280.CrossRefGoogle Scholar
Zhu, X.-K., Yu, C.-P., Tong, F.-L., et al. Numerical study on wall temperature effects on shock wave/turbulent boundary-layer interaction, AIAA J., 2017, 55, (1), pp 1–10.CrossRefGoogle Scholar
Spaid, F.W. and John, C.F. Incipient separation of a supersonic, turbulent boundary layer, including effects of heat transfer, AIAA J., 1972, 10, (7), pp 915–922.CrossRefGoogle Scholar
Back, L.H. and Robert, F.C., Shock wave/turbulent boundary-layer interactions with and without surface cooling, AIAA J., 1976, 14, (4), pp 526–532.CrossRefGoogle Scholar
Bernardini, M., Asproulias, I., Larsson, J., Pirozzoli, S. and Grasso, F. Heat transfer and wall temperature effects in shock wave turbulent boundary layer interactions, Phys. Rev. Fluids, 2016, 1, p 084403.CrossRefGoogle Scholar
Volpiani, P.S., Bernardini, M. and Larsson, J. Effects of a nonadiabatic wall on hypersonic shock/boundary-layer interactions, Phys. Rev. Fluids, 2020, 5, (1), p 014602.CrossRefGoogle Scholar
Souverein, L., Bakker, P. and Dupont, P., A scaling analysis for turbulent shock-wave/boundary-layer interactions, J. Fluid Mech., 2013, 714, (1), pp 505–535.CrossRefGoogle Scholar
Jaunet, V., Debieve, J.F. and Dupont, P. Length scales and time scales of a heated shock-wave/boundary-layer interaction, AIAA J., 2014, 52, (11), pp 2524–2532.CrossRefGoogle Scholar
Zuo, F.-Y., Wei, J.-R, Hu, S.-L., et al. Effects of wall temperature on hypersonic impinging shock-wave/turbulent-boundary-layer interactions, AIAA J., 2022, 60, (9), pp 5109–5122.CrossRefGoogle Scholar
Zhu, K., Jiang, L.X., Liu, W.D., Sun, M.B., Wang, Q.C. and Hu, Z.W. Wall temperature effects on shock wave/turbulent boundary layer interaction via direct numerical simulation, Acta Astronaut., 2021, 178, 499–510.CrossRefGoogle Scholar
Tong, F., Tang, Z., Yu, C., Zhu, X. and Li, X. Numerical analysis of shock wave and supersonic turbulent boundary interaction between adiabatic and cold walls, J. Turbul., 2017, 18, (6), pp 569–588.CrossRefGoogle Scholar
Fu, D., Ma, Y., Li, X., et al., Direct Numerical Simulation of Compressible Turbulence, Science Press, 2010, Beijing, China (in Chinese).Google Scholar
Duan, L., Beekman, I. and Martin, M.P. Direct numerical simulation of hypersonic turbulent boundary layers. Part 2. Effect of wall temperature, J. Fluid Mech., 2010, 655, pp 419–445.CrossRefGoogle Scholar
Pirozzoli, S., Grasso, F. and Gatski, T.B. Direct numerical simulation and analysis of a spatially evolving supersonic turbulent boundary layer at M= 2.25, Phys. Fluids, 2004, 16, (3), pp 530–545.CrossRefGoogle Scholar
Tang, Z., Xu, H., Li, X., et al. Aerodynamic heating in hypersonic shock wave and turbulent boundary layer interaction, J. Fluid Mech., 2024, 999, p A66.CrossRefGoogle Scholar
Tong, F., Yuan, X., Lai, J., et al. Wall heat flux in a supersonic shock wave/turbulent boundary layer interaction, Phys. Fluids, 2022, 34, (6), p 65104.CrossRefGoogle Scholar
Tong, F., Duan, J. and Li, X. Shock wave and turbulent boundary layer interaction in a double compression ramp, Comput. Fluids, 2021, 229, p 105087.CrossRefGoogle Scholar
Li, X., Fu, D., Ma, Y., et al. Direct numerical simulation of shock wave turbulent boundary layer interaction, Sci. Sin., 2010, 40, pp 791–799. (in Chinese)Google Scholar
Ma, C. and Liu, J. Effect of grid strategy on numerical simulation results of aerothermal heating loads over hypersonic blunt bodies, Acta Aeronaut. Astronaut. Sin., 2023, 44, (05), pp 73–86.Google Scholar
Trettel, A. and Larsson, J. Mean velocity scaling for compressible wall turbulence with heat transfer, Phys. Fluids, 2016, 28, (2), p 026102.CrossRefGoogle Scholar
van Driest, E.R. Turbulent boundary layer in compressible fluids, J. Aeronaut. Sci., 1951, 18, pp 145–160.CrossRefGoogle Scholar
Walz, A. Boundary Layers of Flow and Temperature, MIT Press, 1969,Cambridge, MA, USA.Google Scholar
Zhang, Y., Bi, W., Hussain, F. and She, Z. A generalized Reynolds analogy for compressible wall-bounded turbulent flows, J. Fluid Mech., 2014, 739, pp 392–420.CrossRefGoogle Scholar
Chu, Y.-B., Zhuang, Y.-Q. and Lu, X.-Y. Effect of wall temperature on hypersonic turbulent boundary layer, J. Turbul., 2013, 14, (12), pp 37–57.CrossRefGoogle Scholar
Simeonides, G. and Haase, W. Experimental and computational investigations of hypersonic flow about compression ramps, 1995, J. Fluid Mech., 283, pp 17–42.CrossRefGoogle Scholar
De Luca, L., Cardone, G., Aymer De La, C.D., et al. Gortler instability of a hypersonic boundary layer, Exp. Fluids, 1993, 16, pp 10–16.CrossRefGoogle Scholar
Navarro-Martinez, S. and Tutty, O.R. Numerical simulation of Görtler vortices in hypersonic compression ramps, Comput. Fluids, 2005, 34, (2), pp 225–247.CrossRefGoogle Scholar
Spaid, F.W. and Frishett, J.C. Incipient separation of a supersonic, turbulent boundary layer, including effect of heat transfer, AIAA J., 1972, 10, (7), pp 915–922.CrossRefGoogle Scholar
Chapman, D.R., Kuhen, D.M. and Larson, H.K. Investigation on separated flows in supersonic and subsonic streams with emphasis on the effect of transition. NACA TN 3869, 1957.Google Scholar
Schreyer, A.M., Sahoo, D., Williams, O.J.H. and Smits, A.J. Experimental investigation of two hypersonic shock/turbulent boundary-layer interactions, 2018, AIAA J., 56, (12), pp 4830–4844.CrossRefGoogle Scholar
Bhagwandin, V.A., Helm, C.M. and Martin, P. Shock wave-turbulent boundary layer interactions in separated compression corners at Mach 10, in AIAA Scitech 2019 Forum, 2019, San Diego, CA, USA, p 1129.CrossRefGoogle Scholar