Solutions of thin-layer Navier-Stokes equations for missile configurations

Solutions of the thin-layer Navier-Stokes equations have been obtained for two typical missile bodies as well as two complete missile configurations. The finite-differenced three-dimensional equations are solved using a modified NASA Ames solver code on a body-fitted curvilinear grid system developed in conjunction with the flowfield solver. The grid program is based on the method of algebraic interpolation and is capable of generating three-dimensional grid systems for missile bodies and finned-missiles having up to eight control surfaces. 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 present procedures are proven effective in dealing with complete missile configurations flying at high angles of attack. The predicted aerodynamic loading coefficients and pressure distributions match the available wind-tunnel data with good accuracy. Flow non-linearities such as shock, streamwise and cross-flow separations, and reverse flow have been detected and verified with the available experimental reports. Leading-edge separation and classical patterns of vortical flow have also been numerically obtained and studied for interaction effects. The Mach number and Reynold's number effects on the convergence of the numerical process are also discussed.