Experimental investigation of terminal shock sensors in mixed-compression inletsThis 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.
Document ID
19900053505
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sajben, Miklos (McDonnell-Douglas Research Labs. Saint Louis, MO, United States)
Donovan, John F. (McDonnell-Douglas Research Labs. Saint Louis, MO, United States)
Morris, Martin J. (McDonnell Douglas Research Laboratories Saint Louis, MO, United States)