Influence of Geometrical Parameters of Heat Shield on Flow Characteristics at Transonic Mach


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Abstract


The numerical simulation over the bulbous heat shield is carried out by solving time-dependent compressible axisymmetric turbulent Reynolds-averaged Navier-Stokes equations. The solution of these equations is obtained employing the Baldwin-Lomax turbulence model. A three-stage Runge-Kutta time-stepping scheme has been used in conjunction with finite-volume discretization of the computational domain. The flowfield features over the bulbous payload shroud have been analyzed using the density contour plots and surface pressure distributions. Flow separation on the payload shroud due to the terminal shock wave is observed at transonic Mach numbers range. The normal shock movement on the heat shield is simulated for various transonic Mach numbers. The maximum diameter of the various heat shields is kept constant in order to evaluate the movement of terminal shock. A recirculation zone of the flowfield is formed in the boat-tail region of the payload shroud. The density increases ahead of the stagnation region of the heat shield moves close to the heat shield with the increasing transonic Mach number. It also depends on the cone angle of the heat shield as observed in the density contours plots of the flowfield.
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Keywords


Aerodynamics; CFD; Compressible Flow; Transonic; Viscous Flow

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References


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