Three Dimensional Simulation of Supersonic Flow over Missiles of Different Shapes

Abstract

In this work, a three-dimensional primitive variable of supersonic flow over missiles was computed based on finite difference computational fluid dynamic methods. The problem was considered is to deal with external, inviscid, compressible supersonic-flow over three-dimensional missiles with and without canard. Euler equations were solved using time-marching MacCormack's explicit technique. The flow conditions are taken at sea level and Mach number was tested up to 4.0. To deal with complex shape of missiles the so-called "body fitted coordinate system" was considered and the algebraic and elliptic methods were used to generate grids over missiles. The number of iterations and the number of mesh points depending on Mach number. The result indicate, that for the same Mach number, the increasing of mesh points, lead to increase of the number of iterations.