Computation of 3-D transonic flows for wings and wing-body configurations (Closure Report)13;

Three dimensional transonic full potential equation has been solved in conservative and non-conservative forms using SLOR and ADI(AF2) schemes respectively. The corresponding codes SPL022 and STWING have been made operational in ML UNIVAC/1100 computer. These codes were applied to compute transonic flow past ONEBA-M6, Rectangular wings and EAE WING-A. The result were compared with available experimental and numerical results.13; A simple approach has been developed to use the two13; dimensional grid generation method by solving elliptic13; PDEs to generate the three dimensional grid for wing fuselage configurations. This simple method can be applied to generate grids for arbitrary fuselage fitted with any swept wing with dihedral. Three dimensional transonic analysis code STWING, with approximate factorization (AP2) scheme has been suitably used as a flow solver. The results computed for two realistic configurations have been compared with available numerical and experimental results. It has been observed in the present computations that AF2 scheme is not sensitive to grid stretching