03.1 - Aerodynamics – CFD Methods and Validation
NUMERICAL INVESTIGATION OF SHOCKWAVE TURBULENT BOUNDARY LAYER INTERACTION AT MACH 2.5 OVER A COMPRESSION RAMP
S. Gunasekaran, Cranfield Univeristy, United Kingdom; Z.A. Rana, Prince Mohammad Bin Fahd University, Saudi Arabia; S. Prince, Cranfield University, United Kingdom
A canonical shockwave-boundary layer interaction experiment is planned in a small working section supersonic wind tunnel, that will allow detailed measurements of the effects of various surface treatments, such as sand grain roughness, to be acquired to allow for tuning of high fidelity CFD methods. This paper presents preliminary results of a steady CFD campaign to support the design of the experiments, involving the Mach 2.5 flow past a compression ramp to understand the 3D flow behavior in the tunnel test section. The investigation covered various ramp angles and distinct flow regimes, including fully attached flow, small separation bubble and large separation bubble. The pressure distribution over the ramp was examined to determine the positions of the separation and reattachment fronts which will be 3D in nature, in comparison with the purely 2D case. Computational results from Reynolds-averaged Navier-Stokes (RANS) were compared with theoretical solutions. The predicted upstream movement of the separation line on the flat plate, and the downstream movement of the reattachment line on the ramp, allows for the proper placement of the kulite surface pressure sensors for the experimental campaign.
DOI: 10.71945/icas2026_0550