円錐をよぎる極超音速湧出流の実験

抄録

Experiments on a hypersonic source flow past a cone with 15° semivertex angle are made in a conical nozzle of the shock tunnel. The Mach numbers of the oncoming flow at the cone tip are 7.5 and 9.5, respectively. From the measured pressures along the cone surface, it is shown that, although the pressure on the cone surface is kept constant in a uniform supersonic fiow, it is very much decreased when the distance from the nose of the cone, divided by the source-to-nose distance, increases beyond about 0.1 if the cone is in a supersonic source flow.