As flight speeds increase, supersonic aircraft powerplant installations may encounter complex aerodynamic problems due to shock reflection and possibility of inlet shock instability created by pod-to-pod interference; experimental program conducted at United Aircraft Corp and wind tunnel test data obtained during study of adjacent inlet interference are presented; program established, for Mach 3.0 design mixed compression inlet, dividing line between regions of expelled shock interference and completely stable operation; study was also conducted to determine effect of placing plate between pods.
Inlet-to-inlet shock interference tests
NASA CR
NASA Contractor Reports ; n 264
1965
45 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Inlet-to-inlet shock interference tests
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