Effect of tip vortex structure on helicopter noise due to blade-vortex interaction
Open Access
- 1 October 1980
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 17 (10), 705-711
- https://doi.org/10.2514/3.44681
Abstract
No abstract availableKeywords
This publication has 6 references indexed in Scilit:
- Some results of the testing of a full-scale Ogee tip helicopter rotor; acoustics, loads, and performancePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1977
- Helicopter noise - State-of-the-artPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1977
- High frequency thin-airfoil theory for subsonic flowAIAA Journal, 1976
- Calculation of Aircraft Wake Velocity Profiles and Comparisonwith Experimental MeasurementsJournal of Aircraft, 1974
- On the Inviscid Rolled-Up Structure of Lift-Generated VorticesJournal of Aircraft, 1973
- Helicopter Noise due to Blade-Vortex InteractionThe Journal of the Acoustical Society of America, 1971