Unsteady Flow Transition Effects on a Pitching Transonic Laminar Airfoil
Abstract
This paper presents a computational study of unsteady transonic effects on a pitching supercritical laminar airfoil using high-order implicit large-eddy simulation. A CAST10-2 airfoil operating at a chord-based Reynolds number of [Formula: see text], a transonic freestream Mach number of [Formula: see text], and a small nominal angle of attack of [Formula: see text] deg was subjected to forced pitching oscillations about the quarter-chord with a small amplitude of [Formula: see text] deg and reduced frequencies of [Formula: see text], 0.23, and 0.285. Complex interactions between flow separation, the motion of multiple shocks, and excursions of transitional flow were elucidated and compared against inviscid simulations. The boundary layer was found to be highly sensitive to pitch frequency, due in large part to the effects of frequency on shock motion. [Formula: see text] was found to be indirectly affected by the impact of shock motion on the boundary-layer state. Aerodynamic damping diminished with increasing oscillation frequency until becoming negative at [Formula: see text], indicating potential for aeroelastic instability.
Document Details
- Document Type
- Pub Defense Publication
- Publication Date
- Mar 01, 2023
- Source ID
- 10.2514/1.j062380
Entities
People
- Caleb J. Barnes
- Miguel R. Visbal
Organizations
- Air Force Office of Scientific Research
- Air Force Research Laboratory