Affiliation:
1. Department of Mechanical Engineering, Indian Institute of Technology (Indian School of Mines ) Dhanbad, Jharkhand 826004, India
Abstract
A series of implicit large eddy simulations have been conducted to implement thermal control on the transonic shock-boundary layer interactions (SBLIs) over a natural laminar flow airfoil, operating beyond the drag divergence Mach number. The study focuses on the SHM1 airfoil, where the baseline flow exhibits shock-induced separation under specific conditions: free stream Mach number M∞=0.78, angle of attack α=0.38°, and Reynolds number Re=8×106. A time-periodic surface heat flux is introduced, strategically located near the shock structures of the unaltered flow, and the impact of heating vs cooling is investigated through instantaneous Schlieren visualizations and vorticity dynamics, and time-averaged load distributions and boundary layer parameters. Time-averaged Mach contours are utilized to measure the shock strength and extent, revealing that thermal control effectively mitigates the detrimental impact of transonic SBLI on the airfoil's performance. Cooling control emerges as the more effective method, and a case featuring multiple cooling controls near the shock structures demonstrates superior efficacy in controlling shock waves and suppressing shock-induced separation. This optimized configuration results in an improved aerodynamic efficiency of 12.65% compared to the baseline flow.