Development and Validation of a Combined Rotor-Fuselage Induced Flow-Field Computational Method.

Abstract

A potential-flow panel method has been modified to calculate the effects of a rotor wake on the time-averaged surface pressure and velocity distributions on a helicopter fuselage. The rotor-induced velocities are calculated by using a vortex-tube wake model. The calculated pressure distributions are found to compare well with experimental data obtained from tests of a wind-tunnel model. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1980
Accession Number
ADA085968

Entities

People

  • Carl E. Freeman

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Cartesian Coordinates
  • Computational Science
  • Dynamic Pressure
  • Experimental Data
  • Fixed Wing Aircraft
  • Flow
  • Flow Fields
  • Free Stream
  • Hilsch Tubes
  • Numerical Analysis
  • Plastic Explosives
  • Potential Flow
  • Pressure Distribution
  • Static Pressure
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering