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Static internal performance of a two-dimensional convergent nozzle with thrust-vectoring capability up to 60 deg
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Leavitt, L. D. |
| Copyright Year | 1985 |
| Description | An investigation was conducted at wind-off conditions in the static-test facility of the Langley 16-Foot Transonic Tunnel to determine the internal performance characteristics of a two-dimensional convergent nozzle with a thrust-vectoring capability up to 60 deg. Vectoring was accomplished by a downward rotation of a hinged upper convergent flap and a corresponding rotation of a center-pivoted lower convergent flap. The effects of geometric thrust-vector angle and upper-rotating-flap geometry on internal nozzle performance characteristics were investigated. Nozzle pressure ratio was varied from 1.0 (jet off) to approximately 5.0. |
| File Size | 10583014 |
| Page Count | 71 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850010642 |
| Archival Resource Key | ark:/13960/t0gv0gj0q |
| Language | English |
| Publisher Date | 1985-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Hinges Static Pressure Nozzle Geometry Tables Data Nozzle Flow Transonic Wind Tunnels Thrust Vector Control Wind Tunnel Tests Flaps Control Surfaces Nozzle Thrust Coefficients Convergent Nozzles Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
