The present work compares the high resolution schemes of (1) Yee, Warming and Harten, (2) Harten, (3) Yee and Kutler and (4) Hughson and Beran applied to the solution of aeronautical and aerospace problems. All schemes are TVD flux difference splitting type and are second order accurate in space. The Euler equations in conservative form, employing a finite volume formulation and a structured spatial discretization, are solved in two-dimensions. The time integration is performed by a dimensional splitting method and is first order accurate. The steady state physical problems of the supersonic flows along a ramp and around a blunt body configuration are studied. In the ramp problem, the Hughson and Beran scheme was the most critical because presented the most intense pressure field and the most intense Mach number field. Moreover, this scheme predicts the best value to the shock angle of the oblique shock wave. The shock and the expansion fan pressure distributions are better captured by the Yee, Warming and Harten and the Yee and Kutler schemes. In the blunt body problem, the Harten scheme presented the most intense pressure field. The Harten scheme estimates the best value to the stagnation pressure on the configuration nose.
Yee; Warming and Harten algorithm; Harten algorithm; Yee and Kutler algorithm; Hughson and Beran algorithm; Euler equations
