Throat Stability Bypass Systems To Increase The Stable Airflow Range Of A Mach 2 5 Inlet With 60 Percent Internal Contraction
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Distributed Educated Throat Stability Bypass to Increase the Stable Airflow Range of a Mach 2.5 Inlet with 60-percent Internal Contraction
The results of an experimental investigation to increase the stable airflow operating range of a supersonic mixed-compression inlet are presented. A distributed educated throat stability-bypass entrance configuration was tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 16.1 percent was obtained if a constant pressure was maintained in the bypass plenum. Limited unstart angle of attack data are presented.