Abstract
The shape of scramjet-engine utilized for a space vehicle may be unsymmetrical in general. Supersonic flows generated in such unsymmetric nozzle are very unstable due to pseudo-shock waves. In the present study, a flow in an unsymmetrical nozzle was generated by a shock tube. To analyze the effects of the nozzle contour on the flow, three kinds of nozzle configuration were examined experimentally. The interaction of supersonic expansion flows in the nozzle with the boundary layer developed on a nozzle wall was investigated by using a schlieren system, a schlieren interferometer and a Mach-Zehnder interferometer. An Argon-Ion laser with an electro-magnetic shutter (AOM and EOM) as the light source was used in a Mach-Zehnder interferometer. The frequency of the pseudo-shocks was not affected by the flow velocity at the nozzle entrance but was affected by the nozzle configuration.
