NAVIER-STOKES COMPUTATIONS ON FULL WING-BODY CONFIGURATION WITH OSCILLATING CONTROL SURFACES

Unsteady Navier-Stokes simulations have been performed for vortical fl ows over an ''arrow-wing'' configuration of a supersonic transport in the transonic regime. Computed steady pressures and integrated force c oefficients with and without control surface deflection at a moderate angle of attack are compared with experiment. For unsteady cases, osci llating trailing-edge control surfaces are modeled by using moving gri ds. Response characteristics between symmetric and antisymmetric oscil latory motions of the control surfaces on the left and right wings are studied. The antisymmetric case produces higher lift than the steady case with no deflection and the unsteady symmetric case produces highe r lift than the antisymmetric case. The detailed analysis of the wake structure revealed a strong interaction between the primary vortex and the wake vortex sheet from the nap region when the flap is deflected up.