Supersonic shock wave study and wing optimisation of Dassault Rafale military aircraft

Aerodynamic study of Dassault rafale aircraft using computational fluid dynamics method clarified the effect of shock waves encountered by delta wing in cruising supersonic medium. Analysis was carried out by using CAD model of the RAFALE aircraft with analytical calculations of fluid parameters which helped to observe the behaviour of supersonic flow over the selected aircraft. Different supersonic airfoils were used in wing configurations and analysed with suitable boundary condition. Each airfoil with wing considered as different cases. Analytical calculation of flow parameters were determined from the shock angle that has been encountered by the wing section of RAFALE aircraft. These flow parameters further used to decide the characteristic, strength and property of the shock waves. Also helped to conclude the result by comparing the fluid parameters. For futuristic study, supersonic wedge airfoil is introduced and gave promising results for same boundary condition. This study may help in future for optimisation of delta wing for supersonic flow with constant swept back angle.