THE PARAMETRIC ANALYSIS OF FLOW CONTROL METHODS FOR FOREBODY SHOCK STRUCTURES IN SUPERSONIC FLOW FIELD

Abstract

Hypersonic compressible flow fields subject vehicle leading edges to extreme aerodynamic heating due to high-temperature and high-pressure effects. This study focuses on a combined control strategy that integrates passive flow control structures (aerospike and aerodisk) with active flow control through jets to reduce aerodynamic heating and drag. Using numerical simulations with a two-dimensional axisymmetric model and the Reynolds-averaged Navier- Stokes equations combined with the SST turbulence model. The findings indicate that the aerodisk-lateral jet configuration transforms the oblique shock wave into a coherent structure, reducing reattachment shock intensity and enlarging the subsonic recirculation zone at the blunt body’s leading edge. Moreover, increasing the spike's length-to-diameter ratio and moving the aerodisk away from the blunt body further enhances cooling by expanding the recirculation zone and improving gas diffusion. The study concludes that the proposed strategy offers valuable insights for improving thermal protection systems and flow control devices in hypersonic environments, setting the stage for future research in this area.