Minimum-Induced Power Loss of a Helicopter Rotor via Circulation Optimization
Author:
Affiliation:
1. Technion—Israel Institute of Technology, 32000 Haifa, Israel
2. U.S. Army Aviation and Missile Command, NASA Ames Research Center, Moffett Field, California 94035
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.9085
Reference11 articles.
1. Helicopter rotor lift distributions for minimum-induced power loss
2. Optimization of rotor performance in hover using a free wake analysis
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1. Blade Vibration and Its Effect on the Optimal Performance of Helicopter Rotors;Journal of Aircraft;2022-01
2. Minimum Induced Power for a Rotor with a Finite Number of Blades;Journal of Aircraft;2018-03
3. Design, fabrication, and benchtop testing of a helicopter rotor blade section with warp-induced spanwise camber variation;Journal of Intelligent Material Systems and Structures;2014-08-07
4. Use of calculus of variations to determine the shape of hovering rotors of minimum power and its application to micro air vehicles;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2011-10-10
5. A Variational Method for Computing the Optimal Aerodynamic Performance of Conventional and Compound Helicopters;Journal of the American Helicopter Society;2010
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