Abstract
In order to investigate the supersonic flow phenomena related to internal and external flows of high-pressure gas pipeline systems, new air breathing engines and space planes, a new supersonic wind tunnel (pressure-vacuum type, Mach 2.0 and 4.0) was designed and constructed in Muroran Institute of Technology. The cross section of the test section is 8 × 8 cm2, and the working-time of the wind tunnel is 20 s for Mach 4 condition. This paper describes firstly outlines of the new Mach 4 supersonic wind tunnel, and describes secondly the structure and characteristics of the Mach 2 and 4 supersonic flows with pseudo-shock waves in a square duct. The characteristics of the pseudo-shock waves were clarified by color schlieren photographs and duct wall pressure measurements.
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