A computational study of the effect of angles of attack on a double-cone type supersonic inlet with a bleeding system

The flow characteristics of a supersonic inlet with a bleeding system under varying angles of attack are studied by computational 3D turbulent flow analysis. A compressible upwind flux difference-splitting Navier–Stokes method with the k–ω turbulence model is used to analyze the super inlet flowfields. The bleeding system successfully removes the low energy flow from the boundary layer near the throat. The bleeding system enables the supply of more uniform flow at the engine face compared to a supersonic inlet without a bleeding system at the expense of mass flow. More non-uniform flowfields are seen at the Aerodynamic Interface Plane when the angle of attack increases. These non-uniform flowfields at the supersonic engine face degrade engine performance.