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.
The previous theory on the minimum induced drag of nonplanar ground effect wings (GEW) with small tip gaps is extended. This theory has first been originated by KIDA and MIYAI, and is based on the method of matched asymptotic expansions. Many examples are newly solved owing to the present extentions, and summarized in a table.
The flow in the laser cavity of the CO2-N2-He System Gas Dynamic Laser was treated theoretically as one problem of the non-equilibrium radiating gas flow, and the output power of the laser was calculated numerically. On the other hand, the output power was measured by the shock tube and the test results showed that the measured powers agree well with the theoretical ones under the various shock speeds.