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Flight investigation of an air-cooled plug nozzle with afterburning turbojet
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Samanich, N. E. |
| Copyright Year | 1972 |
| Description | A convectively cooled plug nozzle, using 4 percent of the engine air as the coolant, was tested in 1967 K (3540 R) temperature exhaust gas. No significant differences in cooling characteristics existed between flight and static results. At flight speeds above Mach 1.1, nozzle performance was improved by extending the outer shroud. Increasing engine power improved nozzle efficiency considerably more at Mach 1.2 than at 0.9. The effect of nozzle pressure ratio and secondary weight flow on nozzle performance are also presented. |
| File Size | 9583815 |
| Page Count | 57 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720024135 |
| Archival Resource Key | ark:/13960/t2r54d532 |
| Language | English |
| Publisher Date | 1972-09-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Flight Tests Plug Nozzles Transonic Flow Nozzle Thrust Coefficients Afterburning Propulsion System Configurations Turbojet Engines Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
