Unsteady Supersonic Flow over a 2-D Morphing Shock Control Bump Using Different Velocity Profiles

Starting with the simple geometry of a flat plate to study the transient phase of the morphing Shock Control Bump (SCB), this paper presents the results of the second phase of our investigation. The SCB is morphed with different velocity profiles at the optimal morphing time from our previous study. Five motion profiles are tested to morph the SCB, namely; linearmotion, parabolic motion, half-parabolic motion, reversed parabolic motion, and half-reversed parabolic motion. The aim of this paper is to numerically determine the suitable velocity profile that minimizes the entropy losses, the lag effect, and the response time. The 2D supersonicun steady flow with Mꝏ of 2.9 and a Reꝏ of 6.6 × 107 over the morphing bump is simulated by solving the Navier-Stokes equations and using the Arbitrary Lagrangian-Eulerian (ALE)technique. These simulations are conducted using the free open-source Computational Fluid Dynamics (CFD) toolbox, Open FOAM. The investigation is achieved by comparing the lag effect, the entropy losses, and the time response. The results show that the reversed parabolic motion is the favorable one as it provides a short response time, a small lag effect, and low losses. The reason is that at the beginning of the SCB morphing process, the generated shock system from the appearance of SCB is weak which enables a relatively fast motion. However, near the end of the morphing process, the opposite occurs, which requires a relatively slow motion. © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.