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Some Theoretical Considerations of a Stall Proof Airplane
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English
Abstract
For the stall proof airplane there should be a stabilizing pitching moment below the stall angle of attack of sufficient amount to prevent the attainment of the stall angle of attack which cannot be over-ridden by control deflections. This paper presents 1) a development of the moment equations to show the theoretical considerations of a stall proof airplane 2) the nonlinear moment characteristics that must be obtained to satisfy the stall proof requirements. In addition, it is shown that an aerodynamic spoiler located on the under surface of the horizontal tail can be designed to meet these requirements of a stall proof airplane. Wind tunnel results are shown to validate assumptions and predictions.
Authors
Citation
Chevalier, H., "Some Theoretical Considerations of a Stall Proof Airplane," SAE Technical Paper 790604, 1979, https://doi.org/10.4271/790604.Also In
References
- Chevalier Howard L. Brusse Joseph “A Stall/Spin Prevention Device for General-Aviation Aircraft,” SAE paper No. 730333 April 3-6 1973
- Chevalier Howard L. “Aerodynamic Spoiler for Preventing Airplane Stall/Spin Type Accidents,” Final Report No. FAA-RD-75-21 U.S. Dept. of Transportation, Federal Aviation Admin. December 1974
- Barnes C. S. “A Developed Theory of Spoilers on Aerofoils.” July 1965