The Effect of a Simple Throat Distortion on the Downstream Flow in a Hypersonic Wind Tunnel Nozzle
- Creators
- Oliver, R. E.
- Cummings, B. E.
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.
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-PEAttached Files
Submitted - The_Effect_of_a_Simple_Throat_Distortion_on_the_Downstream_Flow_in_a_Hypersonic_Wind_Tunnel_Nozzle.pdf
Files
| Name | Size | Download all |
|---|---|---|
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md5:8aadef097489fc1bb3599b516f31d259
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Additional details
- Eprint ID
- 62671
- Resolver ID
- CaltechAUTHORS:20151207-170857129
- DA-04-495-Ord-19
- U.S. Army Office of Ordnance
- Created
-
2015-12-08Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Hypersonic Research Project
- Series Name
- Hypersonic Research Project Memorandum
- Series Volume or Issue Number
- 34