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Aeropropulsive characteristics of nonaxisymmetric-nozzle thrust reversers at mach numbers from 0 to 1.20
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Capone, F. J. Carson Jr., G. T. Mason, M. L. |
| Copyright Year | 1984 |
| Description | An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the performance of nonaxisymmetric-nozzle thrust reversers installed on a generic twin-engine fighter aircraft model. Test data were obtained at static conditions and at Mach numbers from 0.15 to 1.20 with jet exhaust simulated by high pressure air. Results showed that reverse-thrust levels of greater than 50 percent at static conditions and greater than 30 percent at in-flight conditions could be achieved. Internal reverser-port passage length was found to be very important in improving reverser performance. Increasing the reverser-port passage length improved reverse-thrust performance by as much as 28 percent at static conditions and by as much as 17 percent at Mach 1.20. |
| File Size | 11222643 |
| Page Count | 127 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840016470 |
| Archival Resource Key | ark:/13960/t49p7wf19 |
| Language | English |
| Publisher Date | 1984-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Nozzle Geometry Nozzle Design Aerodynamic Configurations Propulsion System Performance Discharge Coefficient Nozzle Flow Pressure Distribution Thrust Reversal Fighter Aircraft Static Tests Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
