Abstract
This paper presents a computational study of unsteady transonic effects on a supercritical laminar airfoil using high-order implicit large-eddy simulation. The unsteady transitional flow behavior on a static CAST10-2 airfoil operating at a chord-based Reynolds number of , a transonic freestream Mach number of , and several small angles of attack (0 deg ) was examined alongside corresponding inviscid simulations. Shock- and boundary-layer behaviors were found to be rather sensitive, producing significant change in shock structure, flow transition location, and laminar separation bubbles over this small range of . One intermediate case exhibited a buffeting phenomenon in which flow transition alternated between two positions, causing pronounced oscillations in the pitching moment.
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