Transonic Shock Boundary Layer Interaction over SHM-1 and Modified SHM-1 Airfoil

Abstract

In this study, the interaction of transonic shock on boundary layer of twodimensional base SHM-1 airfoil and modified SHM-1 airfoil (with dimples at different locations) has been studied at an angle of attack of 0.38°. The numerical investigation is carried out in Ansys-Fluent at a fixed Reynolds number of 16.2×106 at a Mach number of 0.72 using SST 5�ß “ 5�—ß turbulence model. The results are analyzed in terms of velocity profiles, pressure coefficient, Mach contours. The results demonstrate that the shock wave formed significantly alters the flow characteristics, and this interaction is strongly influenced by the location of the dimple. The maximum dissipation of shock is observed for the dimple at 40% of chord length on the suction side of the SHM-1 airfoil as compared to two other modifications (i.e., 30% chord and 50% chord) by reduction of Mach number from 1.18 to less than 1.13 and weakening of shock strength from 0.4 to 0.14. It was concluded that the aerodynamic performance of the airfoil can be improved by modifying geometry at the location of shockwave formation.