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Numerical Simulation of Shock Wave Turbulent Boundary Layer Interaction over Flat Plate at Mach 6
Numerical simulations of the unsteady compressible Navier–Stokes are carried out for shock wave turbulent boundary layer interaction (SWTBLI) at oblique shock generator of 10° over a flat plate at freestream Mach number 6 for freestream Reynolds number varying from 17.2 × 106, 37.3 × 106 and 72.8 × 106/m and ratio of wall to stagnation temperature of 0.56. This Reynolds number range will produce flow with and without separation caused by an impinging oblique shock wave on a flat plate. MacCormack’s implicit analogue of unsplit explicit finite difference flow solver was employed to solve Reynolds-averaged Navier–Stokes (RANS) equations. The numerical scheme is second-order accurate in spatial and temporal domains. All the essential flow features of SWTBLI are well captured in density and Mach contours. The computed data for time-averaged surface pressure and wall heat transfer coefficient agree with available wind-tunnel data. A relationship between peak surface pressure and wall heat transfer coefficient is obtained at Mach 6. Spectral analysis of time-dependent surface pressure and wall heat flux is presented employing Fast Fourier Transform for Re∞ = 72.8 × 106/m.
Numerical Simulation of Shock Wave Turbulent Boundary Layer Interaction over Flat Plate at Mach 6
Numerical simulations of the unsteady compressible Navier–Stokes are carried out for shock wave turbulent boundary layer interaction (SWTBLI) at oblique shock generator of 10° over a flat plate at freestream Mach number 6 for freestream Reynolds number varying from 17.2 × 106, 37.3 × 106 and 72.8 × 106/m and ratio of wall to stagnation temperature of 0.56. This Reynolds number range will produce flow with and without separation caused by an impinging oblique shock wave on a flat plate. MacCormack’s implicit analogue of unsplit explicit finite difference flow solver was employed to solve Reynolds-averaged Navier–Stokes (RANS) equations. The numerical scheme is second-order accurate in spatial and temporal domains. All the essential flow features of SWTBLI are well captured in density and Mach contours. The computed data for time-averaged surface pressure and wall heat transfer coefficient agree with available wind-tunnel data. A relationship between peak surface pressure and wall heat transfer coefficient is obtained at Mach 6. Spectral analysis of time-dependent surface pressure and wall heat flux is presented employing Fast Fourier Transform for Re∞ = 72.8 × 106/m.
Numerical Simulation of Shock Wave Turbulent Boundary Layer Interaction over Flat Plate at Mach 6
J. Inst. Eng. India Ser. C
Mehta, R. C. (author)
Journal of The Institution of Engineers (India): Series C ; 105 ; 911-920
2024-08-01
10 pages
Article (Journal)
Electronic Resource
English
Numerical Simulation of Shock Wave Turbulent Boundary Layer Interaction over Flat Plate at Mach 6
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