An Experimental Evaluation of a Helicopter Rotor Section Designed by Numerical Optimization.

Abstract

A 10-percent thick helicopter rotor section designed by numerical optimization has been tested at Mach numbers from 0.2 to 0.84 with Reynolds numbers ranging from 1.9 x ten to the 6th power at Mach 0.2 to 4 x ten to the 6th power at Mach numbers above 0.5. The airfoil section exhibited maximum lift coefficients greater than 1.3 at Mach numbers below 0.45 and a drag divergence Mach number of 0.82 for lift coefficients near 0. A moderate 'drag creep' was observed at low lift coefficients for Mach numbers greater than 0.6.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1980
Accession Number
ADA085305

Entities

People

  • R. M. Hicks
  • W. J. Mccroskey

Organizations

  • Ames Research Center

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Flow
  • Geometry
  • Helicopter Rotors
  • High Lift
  • Leading Edges
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Reynolds Number
  • Static Pressure
  • Test And Evaluation
  • Trailing Edges
  • United States

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.