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Theoretical study on regular reflection of shock wave–boundary layer interactions

Published online by Cambridge University Press:  24 July 2020

Longsheng Xue Open the ORCID record for Longsheng Xue [Opens in a new window] ,
Ferry F. J. Schrijer ,
Bas W. van Oudheusden ,
Chengpeng Wang Open the ORCID record for Chengpeng Wang [Opens in a new window] ,
Zhiwei Shi  and
Keming Cheng
Longsheng Xue
Affiliation:
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China Aerospace Engineering Department, Delft University of Technology, Kluyverweg 1, 2629HSDelft, The Netherlands
Ferry F. J. Schrijer
Affiliation:
Aerospace Engineering Department, Delft University of Technology, Kluyverweg 1, 2629HSDelft, The Netherlands
Bas W. van Oudheusden
Affiliation:
Aerospace Engineering Department, Delft University of Technology, Kluyverweg 1, 2629HSDelft, The Netherlands
Chengpeng Wang*
Affiliation:
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China
Zhiwei Shi
Affiliation:
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China
Keming Cheng
Affiliation:
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Yudao Street 29, Nanjing, Jiangsu210016, PR China
*
†Email address for correspondence: [email protected]
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Abstract

In this paper the configurations of shock wave–boundary layer interactions (SWBLI) are studied theoretically and experimentally in Mach number 2 and 2.5 flows on test models with various wedge angles ranging from $9^\circ$ to $21^\circ$. The proposed theoretical method couples the free interaction theory (FIT) with the minimum entropy production (MEP) principle to predict the appearance of separation shock, resulting in convex, straight and concave separation shock waves according to different solution combinations, which agree well with current experiments. Additionally, several influences on SWBLI are studied experimentally, in which the parameters related to theoretical solutions are found mostly determining the flow configuration, and SWBLI is much more sensitive to incident shock strength than incoming flow properties. Separation could be suppressed by incident shock when the MEP solution is smaller than the FIT, while it could be intensified when the MEP solution is larger than FIT; by contrast, the effects of separation position and model mounting height could be very weak.

JFM classification

Boundary Layers: Boundary layer separation Compressible Flows: Shock waves Aerodynamics: High-speed flow
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 899 , 25 September 2020 , A30
Copyright
© The Author(s), 2020. Published by Cambridge University Press

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References

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