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Wind-tunnel investigation of a fowler flap and spoiler for an advanced general aviation wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Paulson Jr., J. W. |
| Copyright Year | 1976 |
| Description | The wing was tested without fuselage or empennage and was fitted with approximately three-quarter span Fowler flaps and half span spoilers. The spoilers were hinged at the 70 percent chord point and vented when the flaps were deflected. Static longitudinal and lateral aerodynamic data were obtained over an angle of attack range of -8 deg to 22 deg for various flap deflections and positions, spoiler geometries, and vent lip geometries. Lateral characteristics indicate that the spoilers are generally adequate for lateral control. In general, the spoiler effectiveness increases with increasing angle of attack, increases with increasing flap deflections, and is influenced by vent lip geometry. In addition, the data show that some two-dimensional effects on spoiler effectiveness are reduced in the three-dimensional case. Results also indicate significant increase in lift coefficient as the Fowler flaps are deflected; when the flap was fully deflected, the maximum wing lift coefficient was increased about 96 percent. |
| File Size | 3624078 |
| Page Count | 81 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760019130 |
| Archival Resource Key | ark:/13960/t8hf2mm9r |
| Language | English |
| Publisher Date | 1976-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Wind Tunnel Stability Tests Flaps Control Surfaces Jet Boundaries Angle of Attack General Aviation Aircraft Lateral Control Graphs Charts Spoilers 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 |
