Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge

摘要

The Second International Vortex Flow Experiment provided a variety of experimental data for a 65° swept delta wing sharp and blunt leading edges. Flow details including forces and moments, surface pressures, Pressure Sensitive Paint measurements, and off-surface flow variables from Particle Image Velocimetry were made available for comparisons with computational simulations. This paper concentrates on some typical problems of delta wings with rounded leading edges at subsonic speed: the prediction of the main leading edge separation, the generation of the second inner vortex, the effect of transition, and Reynolds number effects.