Helicopter Hovering Performance Studies. I. Vortex Wake Analysis. II. Test Facility. III. Blade Tip Pressure Distributions.
Final technical rept. 1 Sep 73-31 Oct 76,
GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
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Results are presented from studies of several problem areas which are related to helicopter hovering performance prediction. A working hypothesis is described for including the tip vortex core effect in a vortex wake analysis and it is shown that the tip vortex geometry in the near wake can be calculated with good accuracy for rotors having fewer than five blades. A hovering model rotor test facility of reduced size is described. Data from this facility include measured pressure distributions on the tip of a single-bladed rotor. Author
- Fluid Mechanics