Tests on probes designed to measure stagnation pressure directly in a supersonic stream

dc.contributor.author	A. R. G. Mundell	en_US
dc.date.accessioned	2014-10-21T15:50:57Z
dc.date.available	2014-10-21T15:50:57Z
dc.date.issued	1973	en_US
dc.identifier.other	ARC/R&M-3755	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3034
dc.description.abstract	The geometry is given of a probe capable of measuring stagnation pressure directly in a supersonic flow, by means of an isentropic compression. Tests have shown that such a probe can indicate the local stagnation pressure to within 0.1 per cent for Mach numbers up to 2.2. Above M = 2.2 the pressure recovery begins to fall from unity and precalibration becomes necessary.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Tests on probes designed to measure stagnation pressure directly in a supersonic stream	en_US