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Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at mach numbers from 0.40 to 0.93 of a 45 degree sweptback wing of aspect ratio 4
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1954 |
| Description | This investigation was made to determine the effects of 6 degree full-spoan and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration. |
| File Size | 42179760 |
| Page Count | 48 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930093721 |
| Archival Resource Key | ark:/13960/t6qz6mx6b |
| Language | English |
| Publisher Date | 1954-02-19 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
