Gust Response Prediction of an Airfoil Using a Modified von Karman-Pohlhausen Technique.

Abstract

An analytical study is presented regarding the theoretical behavior of an airfoil in a pitching airflow. The theoretical development includes the momentum-integral equation for boundary layers in unsteady flow and the von Karman-Pohlhausen integral method for unsteady flow. A computer program was written to model this and was applied to a symmetric Joukowski airfoil. The results of this study show a linear relationship between the increase in the stall angle of attack and the non-dimensional pitch rate.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1982
Accession Number
ADA124716

Entities

People

  • Richard G. Docken Jr

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Computer Programs
  • Computers
  • Equations
  • Flow
  • Flow Fields
  • Flow Separation
  • Incompressible Flow
  • Integral Equations
  • Layers
  • Pressure Gradients
  • Steady Flow
  • Three Dimensional
  • Two Dimensional
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.