Abstract
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 fuselageandacrankedarrowwingwithleading-andtrailing-edge flaps.Numericalsimulationswereconductedand 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 leadingedgevorticeswerereducedbothinsizeandinstrengthbydeflectingtheleading-edge flap,andthedragwasreduced. 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.
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