F314 小型超音速実験機の超音速自然層流翼コンセプトの検証

概要

論文の詳細を見る
Transition on the natural laminar flow wing of a non-powered scaled supersonic experimental airplane was measured by hot-film sensors and an infrared camera at Mach 2. In order to suppress the growth of crossflow instability which dominate the transition on highly swept wing, the pressure falls very rapidly in the vicinity of leading edge of the wing, so as to minimize the crossflow velocity components. The unit Reynolds number had no effect on the transition Reynolds numbers of the wing. The transition Reynolds numbers was 0.8 million at 70% semi-spanwise location at Mach2 at the angle of attack of 2 degrees. We estimated the transition location in quiet high Reynolds number environment at flight by conducting transition measurement in a quiet low Reynolds number wind tunnel and in a variable unit Reynolds number wind tunnel which has moderately low turbulence. The transition at 70% semi-spanwise location at Mach2 at the angle of attack of 2 degrees at flight is predicted to be located downstream of 60 percent chordwise position.
日本流体力学会の論文
2001-07-31