Model Tilt-Rotor Hover Performance and Surface Pressure Measurement

Abstract

A test of a small scale 3-bladed model rotor, with geometry typical of that used on tilt-rotor aircraft, was conducted in the Army Aeroflightdynamics Directorate's anechoic hover chamber. The purpose of this test was to determine the hover performance of the rotor and investigate the pressure distributions on a blade at various collective pitch angles and tip speeds. The measured pressures indicate that the rotor did not stall for high collective pitch angles up to theta sub c = 25 deg. This is clearly a three dimensional effect since two-dimensional theory predicts flow separation at these high angles. The flow near the trailing edge separated above theta sub c = 25 deg which caused a sharp increase in power.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1990
Accession Number
ADA222535

Entities

People

  • Chee Tung
  • Lonnie Branum

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Centrifugal Force
  • Data Acquisition
  • Figure Of Merit
  • Flow Separation
  • Geometry
  • High Angles
  • Leading Edges
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Pressure Transducers
  • Reynolds Number
  • Three Dimensional
  • Tilt Rotor Aircraft
  • Trailing Edges
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Fluid Mechanics and Fluid Dynamics.