CONTINUOUS-OUT PUT TERMINAL-SHOCK-POSITION SENSOR FOR MIXED-COMPRESSION INLETS EVALUATED IN WIND-TUNNEL TESTS OF YF-12 AIRCRAFT INLET

摘要

A new electronic sensor has been built to measure the position of the terminal shock in a supersonic inlet. The sensor uses several static-pressure taps in the inlet wall. The sensor output is continuously proportional to shock position. Previous sensors had dis¬crete output levels that were proportional to shock position. Installed in a YF-12 aircraft flight inlet during wind-tunnel tests, the sensor indicated shock position within ±5 percent of the total distance covered by the static-pressure-tap region. The maximum error caused by an angle-of-attack change of 4° was less than 25 percent. In the region of nor¬mal inlet operation, the angle-of-attack error is negligible. Frequency-response tests show the amplitude ratio is constant out to 60 Hz, and decreases to about 50 percent at 100 Hz, with a phase lag of 50°.