Theoretical Determination of the Lift of a Simulated Ejector Wing.

Abstract

The solution procedure and supporting theory have been developed for calculation of the lift per unit span of an ejector wing model. Model consists of two vortex sheets. A point sink and a point source in a uniform stream. Solution is shown to be dependent on the number of control points used and examples using five control points are presented. A fortran computer program for the Five-Control-Point case is presented. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA124695

Entities

People

  • John T. Domalski

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Air Force
  • Boundary Layer
  • Computer Programs
  • Computers
  • Coordinate Systems
  • Engineering
  • Flow
  • Flow Fields
  • Geometry
  • Leading Edges
  • New York
  • Power Series
  • Three Dimensional
  • Trailing Edges
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.
  • Electromagnetic Wave Scattering and Antenna Radiation Engineering