Abstract

A test program was conducted to investigate performance of lift-engine inlets and to develop a static-test device that would simulate flow distortions at the face of a lift engine. Windtunnel tests indicated that the combination of high forward speed and low engine power would cause flow separation and excessive distortion. A scoop inlet was developed that enabled the flow to turn without separation. For improved pressure recovery in static and near-static operation, longitudinal vanes in the scoop were used to augment the inlet area. By opening the vanes at low speed and closing them for engine restart, acceptable inlet performance was obtained. The wind-tunnel data showed that for a given engine-face velocity the pressure losses, both with and without scoops, were in good agreement when compared at the same approach velocity. This led to the development of a static-test distortion generator that simulated the pressure gradients measured in the wind tunnel. The distortion-generator data agree well with the wind-tunnel data, which indicated that the generator technique should be useful for engine development testing.

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