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Wing Modification for Increased Spin Resistance
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English
Abstract
A simple wing leading-edge modification has been developed that delays outer wing panel stall, thus maintaining roll damping to higher angles of attack and delaying the onset of autorotation. The stall angle of attack of the outer wing panel has been shown to be a function of the spanwise length of the leading-edge modification. The margin of spin resistance provided by the modification is being explored through flight tests. Preliminary results have been used to evaluate spin resistance in terms of the difference in angle of attack between outer wing panel stall and the maxiumum attainable angle of attack.
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Stough, H., DiCarlo, D., and Stewart, E., "Wing Modification for Increased Spin Resistance," SAE Technical Paper 830720, 1983, https://doi.org/10.4271/830720.Also In
References
- Staff of Langley Research Center: Exploratory Study of the Effects of Wing Leading-Edge Modifications on the Stall/Spin Behavior of a Light General Aviation Airplane. NASA TP 1589, 1979
- DiCarlo, Daniel J. Stough, H. Paul III; Patton, James M., Jr. Effects of Discontinuous Drooped Wing Leading-Edge Modification on the Spinning Characteristics of a Low-Wing General Aviation Airplane AIAA Paper 80-1843 1980
- Newsom, W. A. Jr. Satran, D. R. Johnson, J. L. Jr. Effects of Wing Leading-Edge Modifications on a Full-Scale, Low-Wing Airplane—Wind Tunnel Investigation of High Angle-of-Attack Aerodynamic Characteristics NASA TP 2011 1982
- White, E. Richard Wind-Tunnel Investigation of Effects of Wing Leading-Edge Modifications on the High Angle-of-Attack Characteristics of a T-Tail Low-Wing General-Aviation Aircraft NASA CR 3636 1982
- Knight, Montgomery Wind-Tunnel Tests on Autorotation and the "Flat Spin." NACA Report 273 1927