Options
Application of shock-unsteadiness model to interaction of transverse sonic jet and supersonic crossflow
Journal
AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2021
Date Issued
2021-01-01
Author(s)
Vemula, Jagadish Babu
Joshi, Tanisha Kishor
Sinha, Krishnendu
Abstract
Transverse injection of an under-expanded sonic jet into a supersonic crossflow generates a complex flow field. The interaction of the turbulence in the incoming boundary layer and the jet shear layer with the shock waves lies at the heart of the phenomena. In this paper, we study these aspects using the shock-unsteadiness turbulence model that is developed using the physics of shock-turbulence interaction. Reynolds Average Navier-Stokes computations are performed for a sonic jet in a Mach 3.75 crossflow, and the results are compared with the experimental data available in the literature. The effect of the SU correction on the size of the separation bubble, surface pressure, and skin friction coefficient are presented. It is shown to improve results significantly compared to the standard k-ω model, without compressibility correction. The implementation details of the SU model parameters are also discussed.