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A turbojet simulator for mach numbers up to 2.0
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Steffen, F. W. Nosek, S. M. Vanco, M. R. Satmary, E. A. |
| Copyright Year | 1972 |
| Description | A turbojet simulator was designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and termperature. Overall aerodynamic design, compressor operating conditions, automatic controls, turbine aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data. |
| File Size | 4869129 |
| Page Count | 29 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720007142 |
| Archival Resource Key | ark:/13960/t3421qz05 |
| Language | English |
| Publisher Date | 1972-01-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Flight Tests Nozzle Geometry Turbocompressors Transonic Flow Exhaust Nozzles Wind Tunnel Models Simulators Turbojet Engines Axial Flow 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 |
