Preliminary Design Guide for Predicting Rotor Performance.

Abstract

A modified momentum aerodynamic model of a helicopter was used to determine the power required to hover out of ground effect and for level flight at specified velocities. Computations were made for a range of gross weight from 500 to 30,000 pounds, and a range of equivalent flat plate drag areas from 3 to 18 square feet. The results are presented in a graphical format.

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1975
Accession Number
ADA009291

Entities

People

  • Don P. Hodge

Organizations

  • United States Army Materiel Command

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Computations
  • Flight
  • Ground Effect
  • Helicopters
  • Level Flight
  • Momentum
  • Physical Properties

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Dynamics.