A PRESENTATION OF MEASURED AND CALCULATED FULL-SCALE ROTOR BLADE AERODYNAMIC AND STRUCTURAL LOADS

Abstract

A test of a set of Sikorsky CH-34 rotor blades was conducted in the NASA/Ames full-scale wind tunnel at speeds of 110 to 175 knots. One blade of the set was instrumented to measure differential chordwise pressures, as well as flapwise, chordwise and torsional stress. The test results are presented, two- and three-dimensional pressure distributions are compared, and a correlation of airloads and blade stresses is made with a flexible blade aeroelastic theory, including both uniform and variable inflow assumptions. Correlation of airloads and stresses with theoretical results was generally good. Inclusion of variable inflow improved correlation on both advancing and retreating sides of the disk at speeds as high as 175 knots, but the need for a more precise wake treatment is indicated. There is also evidence of a requirement for including lifting surface effects in the calculation at the advancing blade tip. A comparison of some of the wind tunnel data with flight test results shows good agreement.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1966
Accession Number
AD0639981

Entities

People

  • A. A. Lizak
  • J. P. Rabbott Jr.
  • V. M. Paglino

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms
  • Biomedical
  • Weapons Technologies

DTIC Thesaurus Topics

  • Blade Tips
  • Computational Science
  • Control Systems
  • Geometry
  • Lifting Surfaces
  • Mach Number
  • Measurement
  • Military Research
  • Physical Properties
  • Polyethylene Glycols
  • Pressure Distribution
  • Recording Systems
  • Rotary Wing Aircraft
  • Test And Evaluation
  • Three Dimensional
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerodynamics/Aeronautics.