A new probe for the direct measurement of stagnation pressure in supersonic flow

dc.contributor.author	M. J. Goodyer	en_US
dc.date.accessioned	2014-10-21T15:50:59Z
dc.date.available	2014-10-21T15:50:59Z
dc.date.issued	1973	en_US
dc.identifier.other	ARC/R&M-3762	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3041
dc.description.abstract	The probe decelerates a portion of the supersonic free stream into the subsonic range within a distributed compression fan. Stagnation pressure is sampled in the region of subsonic flow using a pitot tube. Pressure recovery has been measured over the Mach number range 1.5 to 2.5, a typical value being 0.999 at a Mach number of 1.88. The probe is usefully insensitive to misalignment with the free stream and pressure tappings in the compression surface allow it to be used also as a flow-direction sensor.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	A new probe for the direct measurement of stagnation pressure in supersonic flow	en_US