CFD analysis of viscous flow over delta-rectangular wing

Aerodynamic analysis of delta wing is necessary to ensure the improvement in performance and maneuverability capabilities of supersonic planes especially fighter aircrafts. Flow analysis of delta wing using computational fluid dynamics (CFD) technique is best alternative to overcome the high cost involved in the conventional wind tunnel testing. In this paper, three dimensional steady state viscous flow analysis over the delta-rectangular wing is performed using numerical technique. This analysis is performed at Mach no. 1.6 and at two different angles of attack using commercial CFD software Ansys-Fluent 14 with Spallart-Allmaras (SA) turbulence model. The computed values of pressure coefficient and lift coefficients are compared with the wind tunnel test values performed by NASA in 1981. The results obtained are found to be in good agreement with wind tunnel test results. Spallart-Allmaras is found to be appropriate turbulence model to capture the viscous flow behavior.