Performance and Pressure Data from a Small Model Tilt-Rotor in Hover.

Abstract

A test of a small three-bladed model rotor, with geometry typical of that used on tilt-rotor aircraft, was conducted in the U.S. Army Aeroflightdynamics Directorate's anechoic hover chamber. The objectives of the test were to determine the hover performance of the rotor and investigate the pressure distributions on a blade operating at various collective pitch angles and tip speeds. This report presents the rotor performance data and blade surface pressures.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1997
Accession Number
ADA324473

Entities

People

  • Chee Tung
  • Lonnie Branum

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airfoils
  • Army Aviation
  • Blade Airfoils
  • Centrifugal Force
  • Classification
  • Data Acquisition
  • Figure Of Merit
  • Geometry
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Pressure Transducers
  • Rotary Wing Aircraft
  • Strain Gages
  • Tilt Rotor Aircraft
  • Transducers

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Fluid Dynamics.