T. Streit

The numerical solution of the Euler and Navier-Stokes system of equations and experimental data for high speed flow around different missile configurations are compared. The configurations are a tangent-ogive-cylinder missile body, a hypersonic missile and a missile with eight fins. The Euler and Navier-Stokes equations are solved with the DLR-CEVCATS finite volume method using multi block mesh structure and multigrid acceleration technique. The numerical solution of the flow equations for these missile configurations has provided a flow with a rich vortex structure and manyfold 3D-effects. The comparison between experimental and Navier-Stokes results for the tangent-ogive-cylinder missile for vortical flow with turbulent and laminar boundary layer are in very good agreement. This validates the CEVCATS code for this type of flow. For the missile with eight fins the aerodynamic coefficients for lift and pitching moment obtained with the Euler solution are in good agreement with experiment and with the Navier-Stokes solution. Therefore, the position of the aerodynamic center is well predicted by the inviscid solution. However this good agreement between viscous and inviscid solution is only obtained for the whole missile, since a separate consideration of forebody and afterbody shows relatively large differences. For the slender hypersonic missile the assumption of inviscid flow leads to an erroneous prediction of the aerodynamic center.

8. DGLR-Fach-Symposium, Köln, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1992, 1992-07, Strömungen mit Ablösung; S.205-214; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics

Bestellbar

1992