Abstract
A supersonic radial flow in a disk channel is studied. Under the high stagnation pressure condition, effects of both the stagnation pressure and the channel height on the radial static pressure distribution are investigated. The pressure recovery through the pseudoshock, its length, the velocity profile and the thickness of the boundary layer were also measured. The results have shown that the supersonic region extends downstream with the increase of the stagnation pressure. However, the transition from the supersonic flow to subsonic flow occurs at the region further upstream than that predicted by the normal shock relation. The pressure recovery through the pseudoshock is found to be lower compared to that of a normal shock, particularly at a high, free-stream Mach number. In addition, the axially asymmetric form of the pseudoshock was observed. Furthermore, the measured static pressure, velocity distribution and the boundary layer thickness at the supersonic region agree well with the results of the two-dimensional calculation.
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