Euler and Navier-Stokes solutions for supersonic flow around a complex missile

Abstract

The numerical solution of the Euler and Navier-Stokes system of equations and experimental data for the supersonic flow around a complex missile configuration are compared. The Euler and Navier-Stokes equations are solved with the DLR finite-volume method CEVCATS using multiblock mesh structure and multigrid acceleration technique. The numerical solution of the flow equations for this missile with eight fins has provided a flow with a rich vortex structure and manifold three-dimensional effects. The aerodynamic coefficients for normal-force and pitching moment obtained with the Euler solution are in good agreement with experimental values. Therefore, the position of the aerodynamic center is wellpredicted by the inviscid solution. However for the flow close to the surface a Navier-Stokes solution is required to obtain agreement with the experimental results.