The Effect of the Delta Wing Vortex System on the Flow around Lifting Surfaces

The vortex structures formed behind a delta wing in supersonic flow are considered. The dependence of these structures on the angle of attack and the oncoming flow Mach number is studied, together with their effect on the aerodynamic properties of a downstream straight wing. The regimes with M = 2 and 3 and α = 10°, 14°, and 20° are considered. The numerical data are obtained using the hybrid multiprocessor supercomputer K-60 system in the Common Use Center of the Keldysh Institute of Applied Mathematics of the Russian Academy of Sciences.