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The Effect of a Simple Throat Distortion on the Downstream Flow in a Hypersonic Wind Tunnel Nozzle

Oliver, R. E. and Cummings, B. E. (1956) The Effect of a Simple Throat Distortion on the Downstream Flow in a Hypersonic Wind Tunnel Nozzle. Hypersonic Research Project Memorandum, 34. California Institute of Technology , Pasadena, CA. (Unpublished) https://resolver.caltech.edu/CaltechAUTHORS:20151207-170857129

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Abstract

An experimental investigation was conducted in the GALCIT 2 1/2" Supersonic Wind Tunnel to determine the effect of a known distortion of the throat section of a hyper sonic nozzle on the flow in the region downstream from the throat. The flow in the nozzle with a rectangular throat section was compared with the flow in the same nozzle with the throat region distorted to produce a throat height which varied linearly across the throat section. The flow was investigated by means of Pitot pressure surveys in the horizontal plane of symmetry of the undistorted nozzle. The magnitude of the effect produced by the throat distortion was observed to be approximately that predicted by one-dimensional isentropic flow relations. However, the sign of the effect was reversed in about the distance required for a curved Mach line to cross the channel.


Item Type:Report or Paper (Technical Report)
Additional Information:ARMY ORDNANCE CONTRACT NO. DA-04-495-Ord-19 Army Project No. 5B0306004 Ordnance Project No. TB3- 0l 18 OOR Project No. 1600-PE
Group:Hypersonic Research Project
Funders:
Funding AgencyGrant Number
U.S. Army Office of OrdnanceDA-04-495-Ord-19
Series Name:Hypersonic Research Project Memorandum
Issue or Number:34
Record Number:CaltechAUTHORS:20151207-170857129
Persistent URL:https://resolver.caltech.edu/CaltechAUTHORS:20151207-170857129
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:62671
Collection:CaltechAUTHORS
Deposited By: Kristin Buxton
Deposited On:08 Dec 2015 22:55
Last Modified:03 Oct 2019 09:21

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