極超音速大迎角翼について

抄録

Experiments on hypersonic flow around a caret wing and a winged-vehicle are conducted by the shock tunnel with conical nozzle, and Mach number of 8. Three force components and surface pressures are measured for a wide range of attack angle up to 45°, and compared with Newtonian flow theory, giving good comparisons for the present, near flatbottomed models, except pitching moments. The source flow produced by the conical nozzle affects measured pressures and forces, and some corrections are necessary.