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Low speed wind tunnel investigation of a four-engine upper surface blown model having swept wing and rectangular and d-shaped exhaust nozzles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sleeman Jr., W. C. Hohlweg, W. C. |
| Copyright Year | 1975 |
| Description | A low speed investigation was conducted in the Langley V/STOL tunnel to determine the power-on static-turning and powered-lift aerodynamic performance of a four engine upper surface blown transport configuration. Initial tests with a D-shaped exhaust nozzle showed relatively poor flow-turning capability, and the D-nozzles were replaced by rectangular nozzles with a width-height ratio of 6.0. The high lift system consisted of a leading edge slat and two different trailing-edge-flap configurations. A double slotted flap with the gaps sealed was investigated and a simple radius flap was also tested. A maximum lift coefficient of approximately 9.3 was obtained for the model with the rectangular exhaust nozzles with both the double slotted flap deflected 50 deg and the radius flap deflected 90 deg. |
| File Size | 4566401 |
| Page Count | 119 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760007998 |
| Archival Resource Key | ark:/13960/t4pk55g82 |
| Language | English |
| Publisher Date | 1975-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Exhaust Nozzles Swept Wings Leading Edge Slats Wind Tunnel Tests Short Takeoff Aircraft Performance Trailing Edge Flaps Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
