Numerical Modeling of the Effect of Supersonic Vortex Structures on the Heat Transfer on the Lifting Surfaces of Flight Vehicles

The simultaneous flow past two rectangular tandem wings is considered. The heat loads on the main wing are studied as functions of the intensity of the vortex formations produced by a generator. The following flow regimes are considered; the freestream Mach number М∞ = 3 and the attack angles of the generator are 10° and 20°. It is shown that under certain conditions the surface temperature of the main wing can be considerably reduced due to its interaction with vortex structures.