Title: Pressure Distribution Measurements in Scramjet Isolators under Asymmetric Supersonic Flow
Abstract: The isolator is an important aerodynamic component of scramjet engine and is used to isolate the inlet from the precombustion pressure rise generated by the combustion process. In typical configuration, the scramjet will be set far back on a hypersonic vehicle, behind a long forebody. This means that flow entering the scramjet inlet will have passed over a substantial length of the vehicle, leading to the formation of a thick boundary layer near the side of the airframe at the entrance of the inlet. The entrance of the isolator is usually situated at the inlet throat. The thick boundary layer on the airframe goes on thickening on the ramp wedge of the inlet, so a thicker boundary layer is formed near the side of the airframe at the isolator entrance. In comparison with the thick boundary layer on the side of the airframe, a thin boundary layer, it starts at the leading edge of the cowl, exists on the side of the cowl at isolator entrance. Therefore the actual flowfield at isolator entrance is asymmetric. Up to now, many researchers have investigated the flow in the isolator under symmetric incoming flow, 1-5 but there has been few papers published focused on the flow analysis in the isolator under asymmetric incoming flow. 6-7 In the present paper, a wind tunnel is designed under asymmetric incoming flow in order to simulate the actual flowfield at the exit of supersonic/hypersonic inlet, and the compression fields in the wind tunnel have been investigated using wall static and pitot pressure measurements. The main objective of the work is to study the effect of the flow asymmetry at the isolator entrance on the pressure rise characteristics and length of the shock train in the isolator.
Publication Year: 2006
Publication Date: 2006-01-09
Language: en
Type: article
Indexed In: ['crossref']
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Cited By Count: 8
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