COMBINED NUMERICAL AND EXPERIMENTAL STUDY OF TRANSONIC VORTICAL FLOWS AROUND MULTI-SWEPT DELTA-WING CONFIGURATIONS

Abstract

The effect of different wing planforms on the aerodynamic behavior of a delta-wing configuration with strakes and leading-edge vortex controls is investigated both, numerically and experimentally. The flow field is dominated by vortex-vortex and vortex-shock interactions as well as by vortex breakdown. Numerical results obtained by URANS and IDDES simulations are compared to integral forces and moments, and to pressures on the leeward side of the model measured in the transonic wind tunnel DNW-TWG. Mach numbers considered are between 0.50 – 2.00 and the angle of attack, α, was varied in the range of 0° ≤ α ≤ 30°, mostly at 0° and 5° sideslip. The Reynolds number was in the range 1.75 – 2.45∙106, depending on Mach number. Results are reviewed and discussed.