INVESTIGATION OF THE FLOW OVER NACELLE/PYLON AND WING CONTROLLED WITH A VORTEX GENERATOR IN HIGH-LIFT CONFIGURATION

摘要

Aerodynamic performance near maximum lift condition of high-lift configuration commercial aircraft model was improved by a kind of vortex generator "chine" installed on the nacelle in lowspeed wind tunnel testing. At first, interference between a nacelle and a main-wing was observed using experimental and also computational results. Then, the optimum location for the chine is explored applying an efficient design process using Generic Algorism (GA) with Kriging surrogate model in the experiment. Results of PIV measurement have clarified how the longitudinal vortex from the chine controls separated flow field structure near the nacelle/pylon and slat-cutoff region.