Unsteady Flow Past a Pitching Airfoil at Moderately High Subsonic Free Stream Mach Numbers.

摘要

An experimental and computational investigation was carried out to study the flow past a NACA 0012 airfoil undergoing pitch up motion at free Mach numbers ranging 0.3 to 0.8. The flow velocity field was captured using PIV demonstrating the ability of the technique to characterize high speed separated flows. A companion computational study was conducted to assess the effect of wind tunnel walls on the dynamic stall process....NACA 0012, Airfoil, Flow Velocity.