Abstract
A numerical analysis has been carried out to investigate turbulent compressible flowfield over a typical bulbous heat shield of a satellite launch vehicle at zero angle of incidence in the Mach number range of 0.8–2.5 and Reynolds number range of 20 × 10 6–25 × 10 6/m. A nonuniform structured grid is employed for numerical discretization. The closure of the system of equations is achieved using a Baldwin-Lomax turbulence model. The numerical procedure employs a multistage Runge-Kutta time-stepping scheme in conjunction with a finite volume method, and is made computationally simple and flexible by linking adjacent sides of the neighbouring cells in the calculation of the viscous terms. Comparisons are made with the available experimental data such as schlieren pictures, oil flow patterns, shock stand-off distance and surface pressure distribution, and are found in good agreement.
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