Oblique Shock-Wave/Boundary-Layer Interaction Using Near-Wall Reynolds-Stress Models

2003 ◽  
Author(s):  
G. Gerolymos ◽  
E. Sauret ◽  
I. Vallet
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Reynolds Stress ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Stress Models ◽  
Wave Boundary

scholarly journals Reynolds-Stress Budgets in an Impinging Shock-Wave/Boundary-Layer Interaction

AIAA Journal ◽  
2019 ◽  
Vol 57 (11) ◽  
pp. 4698-4714 ◽  
Author(s):  
Manan A. Vyas ◽  
Dennis A. Yoder ◽  
Datta V. Gaitonde
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Reynolds Stress ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary ◽  
Stress Budgets

RANS Modelling of Shock-Wave Boundary Layer Interaction in a Mixed Compression Axisymmetric Hypersonic Intake

2016 ◽  
Vol 846 ◽  
pp. 61-66
Author(s):  
Abhijeet Kumar ◽  
Ben Thornber
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Computational Study ◽  
Oblique Shock ◽  
Bow Shock ◽  
Shock Interactions ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

This work focuses on developing a design methodology for a mixed compression axisymmetric hypersonic intake and numerically computing flow around the designed intake using RANS methods to study shock/shock and shock wave/boundary layer interaction. The focus of the computational study is on the effect of increasing the blunt radius of the cowl lip on the resulting shock/shock interaction between the oblique shock emanating from the cone compression apex and the bow shock on the cowl lip; as well the resulting reflected oblique shock boundary layer interaction from the cowl tip onto the cone compression surface. Three (3) radii are tested: 2mm, 16mm and 32mm at Mach 2 and the study is extended to a nominal 16mm condition at Mach 5. It is found that with increasing cowl-lip radius the magnitude of the shock-wave/boundary layer interaction increases significantly. Separation on the cone compression surface is observed at the 16mm and 32mm case at the Mach 2 position and in the 16mm case at the Mach 5 position. In addition in the 16mm and 32mm cases at the Mach 2 position, a Mach stem is observed. The shock/shock interactions, however, are found to be less dramatic. Type III and IV phenomena are observed, however, there is limited interference with the bow shock.

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