Application of the Thin-Layer Navier-Stokes Equations for Missile Aerodynamics

The thin-layer Navier-Stokes equations are solved for complete missile configurations. The conservation form of the three-dimensional equations, written in generalized coordinates, are finite differenced and solved on a body-fitted curvilinear grid system developed in conjunction with the flow solver. The numerical procedure is based on an implicit approximate factorization algorithm employing a multi-grid approach in the simulation of flow about complex finned-missile configurations. The grid program is based on the method interpolation and can automatically produce three dimensional grid systems for missile type bodies and finned-missiles having up to eight control surfaces. The multi-grid method improves the CPU time by a factor of ۴۰ over the conventional single-grid method. This scheme is applied to complete missile configurations in supersonic flow at high angles of attack. The predicted aerodynamic coefficients match the available wind-tunnel data with good accuracy. Flow nonlinearities such as shock and separation are detected and verified with the available experimental reports. Body vortex separation and classical patterns of vortical flow are also numerically detected and examined for vortex interaction effects.