EULER AND NAVIER-STOKES SOLUTIONS FOR SUPERSONIC-FLOW AROUND A COMPLEX MISSILE

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 well-predicted 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.