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Wind-tunnel studies of advanced cargo aircraft concepts. [leading edge vortex flaps for drag reduction
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Rao, D. M. Goglia, G. L. |
| Copyright Year | 1981 |
| Description | Accomplishments in vortex flap research are summarized. A singular feature of the vortex flap is that, throughout the range of angle of attack range, the flow type remains qualitatively unchanged. Accordingly, no large or sudden change in the aerodynamic characteristics, as happens when forcibly maintained attached flow suddenly reverts to separation, will occur with the vortex flap. Typical wind tunnel test data are presented which show the drag reduction potential of the vortex flap concept applied to a supersonic cruise airplane configuration. The new technology offers a means of aerodynamically augmenting roll-control effectiveness on slender wings at higher angles of attack by manipulating the vortex flow generated from leading edge separation. The proposed manipulator takes the form of a flap hinged at or close to the leading edge, normally retracted flush with the wing upper surface to conform to the airfoil shape. |
| File Size | 978053 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810023574 |
| Archival Resource Key | ark:/13960/t8ff8kw9k |
| Language | English |
| Publisher Date | 1981-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Drag Reduction Leading Edge Flaps Supersonic Cruise Aircraft Research Delta Wings Vortex Flaps Wind Tunnel Tests Flow Visualization Aircraft Design Angle of Attack Cargo Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
