Stability of two types of supersonic inlets during a level deceleration flight
The distortion and stability level of a 2-D ramp and a bump supersonic inlet during a level deceleration flight from Mach number 1.5 with the throttle lever pulled in rapidly to Mach number 1.05 were investigated through flight test.Comparison showed that during the deceleration flight,both total pressure distortion and stability margin of the 2-D inlet declined with the decrease of the engine's conversion speed and then kept stable,while distortion of the bump inlet rose first and then declined and then kept stable,and the stability margin first decreased and then increased slightly and then kept stable.In the first half of the deceleration process,distortion of the bump inlet was higher and stability margin of the 2-D inlet decreased more rapidly,but in the second half of the process,distortion of the two types of inlet was close and stability margin was low.Also the analysis revealed that the inlet stability margin calculated only with flow coefficient actually reflected more information about the flow capacity of the inlet other than that calculated with total pressure recovery coefficient and flow coefficient,so the former was recommended to be used as the evaluation index of inlet stability margin.
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万方数据
