Abstract
*† Flow field around a configuratio n of supersonic aircraft with high-lift devices at low speed and high angle of attack is investigated by solving Reynolds-averaged Navier-Stokes equations. The configuration is co nsisted of a fuselage and a cranked arrow wing, with deflected full-span leading edge flaps. Computations are conducted at conditions of the wind-tunnel test, and agreed well with experiment. The effect of the leading edge flap on aerodynamic performance is discussed. D etails of flow field at the design condition are analyzed using computational results to understand the physics of the high lift device. It is confirmed that the aerodynamic performance is improved by deflecting the leading edge flap. The leading edge vortices are reduced both in size and in strength with increase of the flap deflection angle. A typical vortex flap is achieved at a deflection angle. The segment gap of the inboard and outboard leading edge flaps has little influence on the aerodynamic performance.
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