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CFD (Computational Fluid Dynamics) Analysis of Delta wing configurations used for supersonic flight regime is a key area of interest for flow control due to coherent vortical structures existing on the leeward side of wing. In the present research, a numerical study was carried out by using two different turbulence models at Mach No. 1.6, to identify the influence of turbulence modeling and wing on overall pressure distribution and onset of flow separation. Fully structured multi-block grid was used with the grid refinement near the wall to resolve the vortical flow structures accurately. Different turbulence models used were SA (Spalart-Allmaras) and kω-SST (Shear-stress Transport). An under prediction in pressure distribution was observed by using SA Turbulence model, in comparison with known experimental data at fixed Mach No. The analysis of results presented showed that the height of primary vortex increases by increasing the angle of attack and by keeping the Mach No. as fixed. Moreover, the vortex formation on cambered wing seems less pronounced as compared with that of sharp wing at high angle of attack.

Vortical Flow Topology on Windward and Leeward side of Delta Wing at Supersonic Speed