The Use of Source-Sink and Doublet Distributions Extended to the Solution of Arbitrary Boundary Value Problems in Supersonic Flow

Abstract

A direct analogy is established between the use of source-sink and doublet distributions in the solution of arbitrary boundary value problems in subsonic wing theory and the corresponding problems in supersonic theory. The concept of the "finite part" of an integral is introduced and used in the calculation of the improper integrals associated with supersonic doublet distributions. The general equations developed are shown to include several previously published results and particular examples are given for the loading on rolling and pitching triangular wings with supersonic leading edges.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1948
Accession Number
ADA380897

Entities

People

  • Harvard Lomax
  • Max A. Heaslet

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Airfoils
  • Boundary Value Problems
  • Coordinate Systems
  • Delta Wings
  • Differential Equations
  • Equations
  • Fluid Flow
  • Free Stream
  • Leading Edges
  • Lifting Surfaces
  • Load Distribution
  • Partial Differential Equations
  • Pressure Distribution
  • Supersonic Flow
  • Three Dimensional
  • Two Dimensional
  • Wave Equations

Fields of Study

  • Physics

Readers

  • Electromagnetic Wave Scattering and Antenna Radiation Engineering
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics