An Experimental Investigation of High-Speed Rotorcraft Drag

Abstract

An experimental investigation was carried out to determine the effect of subsonic Mach number on the drag characteristics of a high-speed wingless and winged helicopter when equipped with two different rotor head fairings. A simulated unfaired rotor head was provided as a basis for comparison. Test were performed using a 1/9th scale model of a 60,000-pound class helicopter design. Data acquired included gross model force and rotor head force data, wing and pylon surface pressures, and tuft photos.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1972
Accession Number
AD0740771

Entities

People

  • James C. Linville

Organizations

  • United Technologies Corporation

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Boundary Layer
  • Boundary Layer Control
  • Control Systems
  • Drag
  • Dynamic Pressure
  • Fluid Flow
  • Free Stream
  • Helicopters
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Rotary Wing Aircraft
  • Static Pressure
  • Test Facilities
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.
  • Explosive Engineering.