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Experimental Study of Shock Wave Interference Heating on a Cylindrical Leading EdgeAn experimental study of shock wave interference heating on a cylindrical leading edge representative of the cowl of a rectangular hypersonic engine inlet at Mach numbers of 6.3, 6.5, and 8.0 is presented. Stream Reynolds numbers ranged from 0.5 x 106 to 4.9 x 106 per ft. and stream total temperature ranged from 2100 to 3400 R. The model consisted of a 3" dia. cylinder and a shock generation wedge articulated to angles of 10, 12.5, and 15 deg. A fundamental understanding was obtained of the fluid mechanics of shock wave interference induced flow impingement on a cylindrical leading edge and the attendant surface pressure and heat flux distributions. The first detailed heat transfer rate and pressure distributions for two dimensional shock wave interference on a cylinder was provided along with insight into the effects of specific heat variation with temperature on the phenomena. Results show that the flow around a body in hypersonic flow is altered significantly by the shock wave interference pattern that is created by an oblique shock wave from an external source intersecting the bow shock wave produced in front of the body.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Wieting, Allan R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1987
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.15:100484
Accession Number
Funding Number(s)
PROJECT: RTOP 506-40-21-01
Distribution Limits
Work of the US Gov. Public Use Permitted.
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