New Approach for Aerodynamic and Aeroacoustic Analysis of Actively Controlled Flaps Rotor
Author:
Affiliation:
1. Nanjing Tech University, 211816 Jiangsu, People’s Republic of China
2. Tsinghua University, 100084 Beijing, People’s Republic of China
3. AVIC Harbin Aircraft Industry Group Corporation, Heilongjiang 150066, People’s Republic of China
Funder
National Natural Science Foundation of China
the Project of Natural Science Research of Higher Education Institutions of Jiangsu Province
Natural Science Foundation of Jiangsu Province
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.C034225
Reference14 articles.
1. Higher-Harmonic Deployment of Trailing-Edge Flaps for Rotor-Performance Enhancement and Vibration Reduction
2. Wind-Tunnel Testing of Rotor with Individually Controlled Trailing-Edge Flaps for Vibration Reduction
3. MillottT. A.FriedmannP. P. “Vibration Reduction in Helicopter Rotors Using an Actively Controlled Partial Span Trailing Edge Flap Located on the Blade,” NASA CR-4611, 1994.
4. Unsteady aerodynamics of a flapped airfoil in subsonic flow by indicial concepts
5. Application of a New Compressible Time Domain Aerodynamic Model to Vibration Reduction in Helicopters Using an Actively Controlled Flap
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