An Investigation of Transition Fixing Technique for a 10.5% Thick, 28° Sweptback Wing at High Subsonic Speeds and R = 3 x 106

摘要

The results are given of force and pressure measurements on a 10 1/2% thick 28° sweptback wing of modern design mounted on a simplified body with fin. Boundary layer transition on the wing upper surface was left free or fixed by one of two alternative roughness bands.nThe development of regions of separated flow and associated shock wave positions are shown to be very sensitive to transition conditions, particularly when the pressure gradient ahead of the main shock wave is small.