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STOL Tactical Aircraft Investigation
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English
Abstract
Preliminary vehicle-sizing activities and subsequent design update based on related studies, wind tunnel tests, and flight simulations conducted during a STOL Tactical Aircraft Investigation are summarized. The designs developed during Part 1 of the study were based on state-of-the-art technology and powered by scaled derivative engines using existing cores. The three preliminary designs for the lift/propulsion concepts were then updated during Part 2 to complete the study. Resulting point designs are based on data from 1100 h of wind tunnel tests, aerodynamic and stability-and-control methodology development, and stability and flight control technology studies.
Technology developed by Convair Aerospace during the STOL Tactical Aircraft Investigation shows that a light and efficient advanced medium STOL transport can be designed and produced.
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Hebert, J., "STOL Tactical Aircraft Investigation," SAE Technical Paper 730913, 1973, https://doi.org/10.4271/730913.Also In
References
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- Hoerner S. F. “Fluid Dynamics Drag.” 1965
- Hebert J. et al. “Effects of High-Lift Devices on V/ STOL Aircraft Performance.” USAAVLABS Technical Report 70-33A Vol. I Final Report Convair Aerospace Div. of General Dynamics for U.S. Army Aviation Material Laboratories Fort Eustis, Va
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- Vogler R. D. “Wind-Tunnel Investigation of a FourEngine Externally Blowing Jet-Flap STOL Airplane Model.” December 1970
- Gross D. L. “Aircraft Performance Analysis System.” Convair Div. of General Dynamics December 1969
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- “Revision of Takeoff and Landing Ground Rules for STAI.” Garland S. Oates Air Force Flight Dynamics Laboratory (AFSC) July 20 1972
- “Flight Control Technology, Volume V, STOL Tactical Aircraft Investigation.” Convair Aerospace Div. of General Dynamics January 1973