At supersonic Mach numbers, variable geometry is required to provide efficient compression of free-stream air and to match inlet corrected airflow with engine corrected airflow requirements; shock control systems considered; integral control of normal shock position; integral control of normal shock position plus lead compensation; and integral control of normal shock position plus diffuser-exit Mach number anticipation.
Effect of inlet normal shock position control systems on range of supersonic transports
SAE -- Paper
SAE Meeting ; 1961 Inlets
1961
11 pages
Conference paper
English
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Effect of Inlet Normal Shock Position Control Systems on Range of Supersonic Transports
SAE Technical Papers | 1961
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