A Study on the Separation Length of Shock Wave/Turbulent Boundary Layer Interaction

Author:

Zhou Yong-yi1ORCID,Zhao Yi-long2ORCID,Zhao Yu-xin1ORCID

Affiliation:

1. Science and Technology on Scramjet Laboratory, College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, China

2. Unmanned Systems Research Center, National Innovation Institute of Defense Technology, Academy of Military Sciences, Beijing 100071, China

Abstract

The separation length of shock wave/boundary layer interaction (SWBLI) was studied by a numerical method, which was validated by experimental results. The computational domain was two-dimensional (2-D). The flow field was an incident oblique shock interacting with a turbulent boundary layer on a flat adiabatic plate. According to the simulation data, the dependency of the separation length on the relevant flow parameters, such as the incident shock strength, Reynolds number, and Mach number, was analyzed in the range of 2M7. Based on the relations with the flow parameters, two models of the separation length at low and high Mach numbers were proposed, respectively, which can be used to predict the extent of the separation in the SWBLI.

Funder

National Natural Science Foundation of China

Publisher

Hindawi Limited

Subject

Aerospace Engineering

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