Non-adiabatic Wall Effects on Transonic Shock/Boundary Layer Interaction

Direct simulations are carried out to investigate the influence of unsteady heat flux transfer on transonic shock-boundary layer interaction; for flow past SHM-1 airfoil at a free-stream Mach number \(M_{\infty }\) = 0.72 and angle of attack \(\alpha = 0.38^{\circ }\). Flux is added in a periodic manner through a region \((8{-}18\% \; of \;the \;chord)\) located on the suction side of the airfoil, with multiple values of exciter time period \((T_{\text {e}}=2,4)\) considered for our simulation. We show that addition of unsteady heat flux delayed shock formation, along with significant modifications in it’s structure. The time-averaged \(C_{\text {p}}\) distributions revealed a shift in the shock towards the aft, by approximately 5% of the chord; along with an increased lift near the trailing edge, suggesting a nose-down stabilizing influence. Primarily, it is noted that the additional heat flux resulted in an overall increase of the aerodynamic efficiency (lift to drag ratio) by approximately \(10\%\).