A METHOD OF COMPUTING HELICOPTER VORTEX WAKE DISTORTION

Abstract

A method for computing the geometry of the tip vortex of a helicopter rotor in steady, forward flight, including the distortion due to the velocities induced by the vortex wake, was developed. The relative importance of various parameters and approximations used by this method was evaluated for one test case, including comparison with experimental results obtained from a flow visualization study.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
AD0693234

Entities

People

  • Michael P. Scully

Organizations

  • Massachusetts Institute of Technology

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Blade Tips
  • Computer Programs
  • Computers
  • Digital Computers
  • Flight Speeds
  • Flow
  • Flow Visualization
  • Free Stream
  • Geometry
  • Helicopter Rotors
  • Helicopters
  • Lifting Surfaces
  • Rotary Wing Aircraft
  • Time Intervals
  • Trailing Vortices

Fields of Study

  • Physics

Readers

  • Aerodynamics.