Three-component velocity measurement results via stereoscopic PIV for leeward flow of a cranked arrow wing with a centre body are presented in order to understand leeward flow phenomena, emphasizing angle-of-attack effects and Reynolds number effects. The tests are conducted in a low-speed wind tunnel with the Reynolds number range from 0.15 × 106 to 1.5 × 106 at angles of attack of 8° to 20°. Based on instantaneous results, statistical properties such as turbulence kinetic energy are derived. The test results indicate that with increase in angle of attack, interaction between two leading edge separation vortices and a vortex on the body becomes strong, merging into a single vortex. In results on angle of attack effects, vorticity magnitude and kinetic energy have a positive correlation in the cores of the separation vortices. Results of Reynolds number effects show that with increasing Reynolds number, the secondary vortex structure becomes small with the two primary separation vortices moving outward, and the core diameter and vorticity of the vortices become larger and smaller, respectively, due to boundary layer transition on the inboard wing. In general, these Reynolds number effects are similar to the effects of decrease in angle of attack.

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: Wind tunnel tests were conducted to investigate static roll characteristics of an SST model at high angles of attack. The Reynolds number based on the mean aerodynamic chord was 6.2 × 10 4 . Normal force and rolling moment measurements have been done at different roll angles for the cranked arrow wing SST model. Smoke visualizations and Particle Image Velocimetry (PIV) measurements were also performed. Force measurement results were compared both with flow visualization pictures and with PIV measurement results. It was shown that the vortex breakdown has strong influences on the static roll characteristics of the cranked arrow wing.

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