Unsteady Navier-Stokes simulations have been performed for vortical flows over an “arrow-wing” configuration of a supersonic transport in the transonic regime. Computed steady pressures and integrated force coefficients with and without control surface deflection at a moderate angle of attack are compared with experiment. For unsteady cases, oscillating trailing-edge control surfaces are modeled by using moving grids. Response characteristics between symmetric and anti-symmetric oscillatory motions of the control surfaces on the left and right wings are studied. The anti-symmetric case produces higher lift than the steady case with no deflection, and the unsteady symmetric case produces higher lift than the anti-symmetric case. The detailed analysis of the wake structure revealed a strong interaction between the primary vortex and the wake vortex sheet from the flap region when the flap is deflected up.
|Number of pages||11|
|Publication status||Published - 1993 Jan 1|
|Event||Flight Simulation and Technologies, 1993 - Monterey, United States|
Duration: 1993 Aug 9 → 1993 Aug 11
|Other||Flight Simulation and Technologies, 1993|
|Period||93/8/9 → 93/8/11|
ASJC Scopus subject areas