Helicopter Rotor Wake Geometry and Airloads and Helicopter Rotor Wakes
Final scientific technical rept. 6 Jun 1971-6 Jun 1972
MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
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Computer programs have been developed for the calculation of helicopter rotor tip vortex geometry in hover and forward flight and for the calculation of helicopter rotor harmonic airloads in forward flight. Calculated forward flight tip vortex geometries compare well in general with experimental smoke studies although there are differences in detail. The hovering tip vortex geometry agrees qualitatively with experiment but does not move downward fast enough. Airloads were computed using both the classical rigid wake assumption and the distorted tip vortex geometry obtained from the computer program. When compared with experimental airloads measurements the rigid wake airloads give better results than the distorted wake airloads.
- Test Facilities, Equipment and Methods
- Fluid Mechanics