Abstract
Abstract Transonic flows around a rocket were computed using the second-order TVD scheme proposed by Harten for solving the two- and three-dimensional unsteady, compressible Navier-Stokes equations in the conservation-law form. LU -ADI and DD -ADI schemes were employed to the implicit part. The influences of the Reynolds number on the shock-wave/boundary-layer and the shock-wave/vortex interaction were clarified by the two-dimensional analysis. The three-dimensional computations show that there is no stationary shock-wave except near the nose cone. In the wake region, a pair of asymmetrical vortices separates periodically, and the shear layer oscillates. The computed pressure distribution on the surface of the body was compared with that of the three-dimensional experiment. The qualitative agreement of the general profile was good.
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