Flow Simulation of a Supersonic Transport Configuration at Low-Speed and. High-Lift Conditions

The flowfield around a supersonic transport configuration with high-lift devices at a low speed and high angle of attack was investigated by solving Reynolds-averaged Navier-Stokes equations. The configuration consisted of a fuselage and a cranked arrow wing with leading-and trailing-edge flaps. Numerical simulations were conducted and validated at conditions of the wind-tunnel test. Details of the flowfield at the design condition were analyzed using computational results. The effect of the high-lift devices on aerodynamic performance was discussed. The leading-edge vortices were reduced both in size and in strength by deflecting the leading-edge flap, and the drag was reduced. The trailing-edge flap increased the effective camber of the wing and improved the lift force. A typical leading-edge vortex flap was confirmed. It was shown that the aerodynamic performance could be improved by deflecting the leading-and trailing-edge flaps.