Computational Study of Subsonic Flow over a Delta Canard-Wing-Body Configuration

摘要

Subsonic flowfields over a close-coupled, delta canard-wing-body configuration at angles of attack of 20, 24.2, and 30 deg are computed using the OVERFLOW Navier-Stokes solver. Computed flowfields are presented in terms of particle traces, surface streamlines, and leeward-side surface pressure distributions for the canard-on and -off configurations. The interaction between the canard and the wing vortices, wing vortex breakdown, and the influence of the canard on vortex breakdown are identified. The comparison of the pressure data with the available experimental data at Re = 0.32 x 10~6 and Re = 1.4 x 10~6 shows a significant Reynolds-number dependence. Good agreement is obtained with the experiment for the canard-off configuration at all three angles of attack, and for the canard-on configuration at 20-deg angle of attack.