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 2≤M≤7. 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.
Highlights
The prediction of the shock wave/boundary layer interaction (SWBLI) is a formidable challenge for the supersonic and hypersonic aircraft engineer [1]
The compressible Reynolds-averaged Navier-Stokes equations were solved in the numerical simulation which was verified by the experiments
The study focused on the separation length of the SWBLI in a wide range of Mach numbers (2 ≤ M1 ≤ 7)
Summary
The prediction of the SWBLI is a formidable challenge for the supersonic and hypersonic aircraft engineer [1]. Davis and Sturtevant [11] studied the separation length of the laminar boundary layer in high enthalpy compression corner flow. Settles et al [12] studied the turbulent separation length of compression corner flow at Mach 3. Zheltovodov et al [13] investigated the SWBLI in the 2-D compression corner flow experimentally and established the relationship between the separation length and Reynolds number. We analyze the separation length in 2-D incident shock-induced turbulent boundary layer separation in a wide range of Mach numbers (2 ≤ M1 ≤ 7). Two mathematical models are proposed to predict the separation length at low and high Mach numbers
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