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Investigation of installation effects of single-engine convergent-divergent nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Berrier, B. L. Burley II, J. R. |
| Copyright Year | 1982 |
| Description | An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on single-engine convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, at angles of attack from -3 degrees to 9 degrees, and at nozzle pressure ratios from 1.0 (jet off) to 8.0. The effects of empennage arrangement, nozzle length, a cusp fairing, and afterbody closure on total aft-end drag coefficient and component drag coefficients were investigated. Basic lift- and drag-coefficient data and external static-pressure distributions on the nozzle and afterbody are presented and discussed. |
| File Size | 25584685 |
| Page Count | 235 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830002789 |
| Archival Resource Key | ark:/13960/t0004zr0r |
| Language | English |
| Publisher Date | 1982-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Aerodynamic Drag Supersonic Aircraft Fairings Transonic Wind Tunnels Wind Tunnel Tests Convergent-divergent Nozzles Aerodynamic Coefficients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
