Rotor Induced Power

Abstract

Methodology is presented for rapid estimation of the induced power requirements of a helicopter rotor. Operating ranges treated are hover in or out of ground effect, vertical climb, and level flight. Earlier work on this subject is modified by more recent flight test information on ground effect; enlarged in scope by the consideration of a generalized trapezoidal inflow velocity scope by the consideration of a generalized trapezoidal inflow velocity distribution at the rotor; and refined to account for the influence of level flight on the effect of a non-uniform induced velocity distribution at the rotor.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1975
Accession Number
ADA011270

Entities

People

  • Milton A. Schwartzberg

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Army Aviation
  • Circular Wings
  • Coefficients
  • Equations
  • Experimental Data
  • Flight
  • Flow
  • Geometry
  • Ground Effect
  • Helicopter Rotors
  • Helicopters
  • Hovering
  • Level Flight
  • Power
  • Rotary Wing Aircraft

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Plasma Physics / Magnetohydrodynamics
  • Theoretical Analysis.