A THROAT-BYPASS STABILITY-BLEED SYSTEM USING RELIEF VALVES TO INCREASE THE TRANSIENT STABILITY OF A MIXED-COMPRESSION INLET

摘要

This report presents the transient performance of a stability-bleed system installed in a YF-12 flight inlet that was subjected to internal and external airflow disturbances in the NASA Lewis 10- by 10-Foot Supersonic Wind Tunnel. This stability-bleed system could actually be flown on the YF-12 aircraft, because it was designed to fit within the YF-12 inlet structure and to withstand the YF-12 flight environment. The purpose of the system is to allow higher inlet performance wile maintaining a substantial tolerance (without upstart) to internal and external disturbances At Mach numbers of 2. 47 and 2 76, the stability-bleed system increased the inlet tolerance to decreases in diffuser-exit corrected airflow by approximately 10 percent of the operating-point airflow The stability-bleed system complemented the terminal-shock-control system of the inlet and did not show interaction problems