Energy input influence on aerodynamic characteristics and heat flux occuring at 3D supersonic flow past a model aircraft

Numerical simulation of a viscous heat-conducting supersonic (M=2.5) three-dimensional gas flow past a model aircraft (spherically blunted cylinder with wings and tail fins) with energy input into the area in front of it is carried out. Simulations were performed using unsteady Reynolds-averaged Navier-Stokes equations (URANS) and Spalart-Allmaras (SA) turbulence model. Influence of attack angle, energy input’s parameters and placement on the model’s aerodynamic characteristics (wave drag and lift) and heat flux on its surface is determined.