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Investigation of axisymmetric and nonaxisymmetric nozzles installed on a 0.10 scale f-18 prototype airplane model. [wind tunnel tests
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Berrier, B. L. Capone, F. J. |
| Copyright Year | 1980 |
| Description | The Langley 16 foot transonic tunnel was used to investigate the afterbody/nozzle longitudinal aerodynamic characteristics of three different two dimensional nozzles and a base-line axisymmetric nozzle installed on a 0.10 scale model of the F-18 airplane. The effects of thrust vectoring and in-flight thrust reversing were also studied. Horizontal-tail deflections of 0 deg, -2 deg, and -5 deg were tested. Test data were obtained at static conditions and at Mach numbers from 0.60 to 1.20 over an angle-of-attack range from -2 deg to 10 deg. Nozzle pressure ratio was varied from jet off to about 10. |
| File Size | 24952569 |
| Page Count | 305 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800015775 |
| Archival Resource Key | ark:/13960/t1dk07q8t |
| Language | English |
| Publisher Date | 1980-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aircraft Models Nozzle Geometry Nozzle Flow Scale Models Transonic Wind Tunnels Afterbodies Wind Tunnel Tests Thrust Reversal F-18 Aircraft Aerodynamic Characteristics Thrust Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
