An Integral Equation for the Linearized Unsteady Supersonic Flow Over a Wing.

Abstract

This report derives an integral equation for the linearized supersonic unsteady potential flow over a wing. Every integral equation formulation for a problem that appears originally in the form of a partial differential equation presupposes the availability of a fundamental solution. Such a fundamental solution is available for the problem at hand in the literature. It is rederived here to show its particular properties. The integral equation originally obtained requires hat one carry out a limiting process in which one approaches the planform from above or below. This formulation is brought into a form in which this limiting process no longer appears and one works solely with information available at the planform. Examples which can be treated analytically bring some properties which have a bearing on a numerical approach into sharper focus. Keywords: Time dependent, Linearized potential flow, Integral equation, Fundamental solutions, Unsteady aerodynamics.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1987
Accession Number
ADA193773

Entities

People

  • Karl G. Guderley

Organizations

  • University of Dayton

Tags

Communities of Interest

  • Air Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Classification
  • Coordinate Systems
  • Delta Functions
  • Differential Equations
  • Equations
  • Integral Equations
  • Leading Edges
  • Mass Flow
  • Numbers
  • Partial Differential Equations
  • Potential Flow
  • Security
  • Square Roots
  • Two Dimensional
  • Universities

Fields of Study

  • Mathematics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Systems Analysis and Design

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers