Minimum Induced Power for a Rotor with a Finite Number of Blades
Author:
Affiliation:
1. Washington University in St. Louis, St. Louis, Missouri 63130
Funder
Georgia Tech/Washington University Rotorcraft Centers of Excellence Program through a subcontract from Georgia Tech
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.C034423
Reference8 articles.
1. Helicopter rotor lift distributions for minimum-induced power loss
2. Minimum-Induced Power Loss of a Helicopter Rotor via Circulation Optimization
3. A Variational Method for Computing the Optimal Aerodynamic Performance of Conventional and Compound Helicopters
4. HeC. J. “Development and Applications of a Generalized Dynamic Wake Theory for Lifting Rotors,” Ph.D. Dissertation, Georgia Inst. of Technology, Atlanta, GA, Aug. 1989.
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1. Blade Vibration and Its Effect on the Optimal Performance of Helicopter Rotors;Journal of Aircraft;2022-01
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