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Leading edge flap system for aircraft control augmentation
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1984 |
| Description | Traditional roll control systems such as ailerons, elevons or spoilers are least effective at high angles of attack due to boundary layer separation over the wing. This invention uses independently deployed leading edge flaps on the upper surfaces of vortex stabilized wings to shift the center of lift outboard. A rolling moment is created that is used to control roll in flight at high angles of attack. The effectiveness of the rolling moment increases linearly with angle of attack. No adverse yaw effects are induced. In an alternate mode of operation, both leading edge flaps are deployed together at cruise speeds to create a very effective airbrake without appreciable modification in pitching moment. Little trim change is required. |
| File Size | 473120 |
| Page Count | 8 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850011675 |
| Archival Resource Key | ark:/13960/t6547jm6m |
| Language | English |
| Publisher Date | 1984-12-04 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Leading Edge Flaps Vortices Wind Tunnel Tests Stability Augmentation Aircraft Brakes Roll Angle of Attack Lateral Control Rolling Moments Lift Aircraft Control Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
