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Distributed Porous Throat Stability Bypass to Increase the Stable Airflow Range of a Mach 2.5 Inlet with 60 Percent Internal Contraction

Robert Joseph ShawGlenn A. MitchellBobby W. Sanders

出版	National Aeronautics and Space Administration, 1974
URL	http://books.google.com.hk/books?id=JUUg-wnP77UC&hl=&source=gbs_api

註釋The results of an experimental investigation to increase the stable airflow operating range of a supersonic, mixed-compression inlet with 60-percent internal contraction are presented. Various distributed-porous, throat stability-bypass entrance configurations were tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 25 percent was obtained with the optimum configuration if a constant pressure was maintained in the by-pass plenum. The location of the centerbody bleed region had a decided effect on the overall inlet performance. Limited unstart angle-of-attack data are presented.