Investigation of Shock Diffusers at Mach Number 1.85. 1 - Projecting Single Shock Cones
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS CLEVELAND OH LEWIS FLIGHT PROPULSION LAB
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Design conditions for optimum performance of shock diffusers are determined. Single-shock cones used had angles varying from 20 to 70 deg Fahrenheit. Each cone was tested with curved and straight diffusers-inlet sections. Effect of angle of attack was investigated for several configurations. Maximum total-pressure recovery was obtained with 50 deg Fahrenheit cone using straight inlet. Highest total-pressure recoveries were attained with subsonic entrance flow. Variation of maximum total-pressure recovery with cone angle concurred with theoretical analyses.