Performance and Loads Data from a Wind Tunnel Test of a Full-Scale, Coaxial, Hingeless Rotor Helicopter.

Abstract

A test of a full-scale XH-59A Advancing Blade Concept Helicopter was conducted in Ames Research Center's 40- by 80-Foot Wind Tunnel. The helicopter was tested with the rotor on and off, rotor hub fairings on and off, inter-rotor shaft fairing on and off, rotor instrumentation module on and off, and auxiliary propulsion thrust on and off. The investigation was accomplished over an advance ratio range of 0.25 and 0.45 with the rotor on and from 60 to 180 knots with the rotor off. This report presents data on aerodynamic forces and moments, rotor loads, rotor control positions and vibration for the XH-59A as well as the aerodynamic performance of the isolated rotor. (author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1981
Accession Number
ADA110278

Entities

People

  • Fort F. Felker Iii

Organizations

  • Ames Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Forces
  • Aircrafts
  • Airframes
  • Engines
  • Free Stream
  • Fuselages
  • Helicopters
  • Instrumentation
  • Mach Number
  • Plastic Explosives
  • Propulsion Systems
  • Trailing Edges
  • United States
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering