Accession Number:

ADA034093

Title:

Helicopter Hovering Performance Studies. I. Vortex Wake Analysis. II. Test Facility. III. Blade Tip Pressure Distributions.

Descriptive Note:

Final technical rept. 1 Sep 73-31 Oct 76,

Corporate Author:

GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING

Report Date:

1976-10-01

Pagination or Media Count:

80.0

Abstract:

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

Subject Categories:

  • Helicopters
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE