Experimental Investigation on the Influence of Yaw Angle on the Inlet Performance at Mach 7

Kurzfassung

This paper presents the results of an extensive measurement campaign that was conducted with an two-dimensional hypersonic inlet in the Hypersonic Windtunnel H2K at the German Aerospace Center in Cologne in order to study the effects of angle of yaw on the inlet performance. Both the external and internal flow paths of the inlet have been analyzed. Conducted measurements include static and Pitot pressure measurements, shadowgraph imagery, IR-thermography, Mach number and mass flow measurements. To simulate the behaviour of the inlet at different operating points, a throttle was used to impose different backpressures on the inlet.