Experimental investigation of terminal shock sensors in mixed-compression inlets
Abstract
This paper describes experimental investigations of devices designed for the nonintrusive detection of terminal shock location in mixed-compression inlets at high supersonic flight speeds. Systems based on sensing wall pressures by an array of wall-mounted transducers were selected for detailed study. Pressure signals were processed by three different methods: (1) interpretation of instantaneous pressure distributions, (2) detection of the turbulent intensity amplification occurring at the shock, and (3) determination of the upstream limit to which a search-tone, introduced at the downstream end of the channel, can propagate. The first two of these methods were tested in real time. The third method appeared feasible for weak shocks only; at high shock strengths, propagation upstream of the source could not be detected.
- Publication:
-
AIAA, SAE, ASME, and ASEE, 26th Joint Propulsion Conference
- Pub Date:
- July 1990
- Bibcode:
- 1990jpof.confQ....S
- Keywords:
-
- Inlet Pressure;
- Normal Shock Waves;
- Pressure Sensors;
- Supersonic Inlets;
- Wall Pressure;
- Inlet Nozzles;
- Mach Number;
- Pressure Distribution;
- Pressure Measurement;
- Schlieren Photography;
- Instrumentation and Photography