Internal Aerodynamics of Turbojet Test Cells
| dc.contributor.author | Speakman, G. C. | |
| dc.contributor.author | Hayes, J. D. | |
| dc.contributor.author | Netzer, D. W. | |
| dc.date.accessioned | 2013-08-14T17:17:55Z | |
| dc.date.available | 2013-08-14T17:17:55Z | |
| dc.date.issued | 1976-12 | |
| dc.identifier.uri | https://hdl.handle.net/10945/35242 | |
| dc.description | Reproduction of all or part of this report is authorized. | en_US |
| dc.description.abstract | Elliptic computer codes have been developed (including plot routines) which can be used to study the flow field in test cells and exhaust stacks and in the augmenter tube for low thrust operation. The effects of engine-augmenter spacing, augmenter diameter and inlet design, aft cell wall location, test cell by-pass ratio, call inlet conditions and stack-augmenter geometry on the flow field and augmenter pressure rise have been calculated. The models appear to be qualitatively correct and adequate for their intended purposes but model validation with experiment is required. | en_US |
| dc.description.sponsorship | The work reported herein was supported by the Naval Air Propulsion Test Center, Trenton, New Jersey, and the Naval Environmental Protection Data Support Service. | en_US |
| dc.language.iso | en_US | |
| dc.publisher | Monterey, California: Naval Postgraduate School. | en_US |
| dc.subject | Turbojet Test Cell | en_US |
| dc.subject | Augmenter | en_US |
| dc.subject | Flow Model | en_US |
| dc.title | Internal Aerodynamics of Turbojet Test Cells | en_US |
| dc.type | Technical Report | en_US |
| dc.contributor.secondreader | Bell, R. W. | |
| dc.contributor.department | Aeronautics | |
| dc.identifier.npsreport | NPS-67Nt76121 | |
| dc.description.distributionstatement | Approved for public release; distribution is unlimited. |
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