Transonic Wind Tunnel Test of Wing Oscillating in Pitch

摘要

A transonic wind tunnel test was conceived to measure the unsteady pressure distributions of a wing model oscillating in pitch. The test covered the Mach range of 0.50 to 0.90 and the reduced frequency range of 0.0 to 0.25. This paper presents the model description, the wind tunnel test setup and planning, selected experimental results and a preliminary comparison with CFD results solving Reynolds Averaged Navier-Stokes equations. In general, a good matching between CFD and tunnel data was obtained, and some points of improvement were identified for the CFD simulations.