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Effects of installation of f101 dfe exhaust nozzles on the afterbody-nozzle characteristics of the f-14 airplane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Carlson, J. R. Reubush, D. E. |
| Copyright Year | 1982 |
| Description | A wind-tunnel investigation was conducted to determine the effects of F101 DFE (derivative fighter engine) nozzle axial positioning on the afterbody-nozzle longitudinal aerodynamic characteristics of the F-14 airplane. The model was tested in the Langley 16-Foot Transonic Tunnel at Mach numbers from 0.7 to 1.25 and angles of attack from about -2 to 6 degrees. Compressed air was used to simulate nozzle exhaust flow at jet total-pressure ratios from 1 (jet off) to about 8. The results of the investigation show that for subsonic Mach numbers the intermediate cruise nozzle position of the three positions tested resulted in the lowest drag. |
| File Size | 9688881 |
| Page Count | 136 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820011307 |
| Archival Resource Key | ark:/13960/t6tx8571x |
| Language | English |
| Publisher Date | 1982-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aerodynamic Drag F-14 Aircraft Exhaust Nozzles Exhaust Flow Simulation Nozzle Flow Transonic Wind Tunnels Wind Tunnel Tests Wind Tunnel Models Aerodynamic Characteristics Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
