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Compound Tilting Wing for STOL Configurations
Technical Paper
1999-01-5654
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
An empirically based, analytical tool for calculating lift, drag and pitching moment of tilting wing configurations is presented, and used to develop the general characteristics of the Compound Tilting Wing (CTW), a variation on the conventional tilting wing configuration. The CTW utilizes an inboard leading edge extension, which acts as a canard when the wing tilts to augment pitch control during low speed operations and conforms to the wing at zero tilt. This scheme allows the designer more degrees of freedom for overall configuration layout and propulsion system integration for STOL design.
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Citation
Shenk, B., "Compound Tilting Wing for STOL Configurations," SAE Technical Paper 1999-01-5654, 1999, https://doi.org/10.4271/1999-01-5654.Also In
References
- USAF Stability and Control DATCOM
- McCormack, B. Aerodynamics of V/STOL Flight AcademicPress 1967