Simulation on Three-Dimensional Shock Interactions and Aerodynamic Heating Between Body and Wing

This study investigates the flowfield patterns and distributions of surface heat flux due to interactions among three-dimensional shock waves at the junction of the body and wing of an aircraft by solving Reynolds-averaged Navier-Stokes equations at a Mach number of 10 and attack angles ranging from 5 degrees to 20 degrees. The results indicate that the structures of wing/body-shock interactions vary significantly with test conditions. Four types of shock interaction patterns were observed: interaction-free, type I regular, type II regular, and Mach interactions. Once the flowfield of the shock interactions had been established, aerodynamic heating loads of the wing and body were affected by the flowfield structures. Wing/body-shock interactions produced uneven heat flux distributions on the surface and caused an abnormally high heat flux at a localized position. Five profiles of the distribution of heat flux were extracted to describe its characteristics on the surface according to the position and magnitude of the peaks of the localized heat flux. Induction-related factors that led to the peaks were classified into three types: reflected shock/boundary-layer interaction, contact surface impinging, and contact surface grazing.