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

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)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1976
Accession Number
ADA034093

Entities

People

  • George T. Bird
  • Howard M. Mcmahon
  • John G. Palfery
  • Robin B. Gray
  • Satish S. Samant

Organizations

  • Georgia Tech

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Acquisition
  • Aerodynamic Loading
  • Blade Tips
  • Boundary Layer
  • Data Acquisition
  • Engineering
  • Flow Fields
  • Flow Visualization
  • Geometry
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Pressure Transducers
  • Strain Gages
  • Test Facilities
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Materials Science (Mechanical Engineering).
  • Tribology (the study of the boundary interaction between sliding surfaces, lubrication, wear and friction).