Analysis of the Hover Performance of a High Speed Circulation Control Rotor

Abstract

A method for calculating the detailed hover performance of any arbitrary circulation control rotor is presented. The method includes such higher order effects as non-uniform inflow, internal ducting losses and experimental airfoil data. Calculations were performed on an untwisted constant chord blade with varying section thickness and camber. Hover Figures of Merit exceeding 0.80 are calculated for this rotor at thrust coefficient to solidity ratios of 0.20. The optimum pitch angle is determined for each thrust coefficient. The effects of slot height and tip Mach number are also analyzed. A comparison is made with a conventional rotor system of the same solidity.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1971
Accession Number
AD0904474

Entities

People

  • David W Taylor
  • Robert M. Williams

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautics
  • Air Force
  • Aircrafts
  • Computer Programs
  • Figure Of Merit
  • Flow Rate
  • Fluid Dynamics
  • Helicopter Rotors
  • Mach Number
  • Military Research
  • Navy
  • Short Takeoff Aircraft
  • Test And Evaluation
  • Two Dimensional
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.