Second Approximation to Conical Flows

Abstract

The method of expansion in powers of a thickness parameter is employed to calculate supersonic, inviscid flow about symmetrical arrow-head wings lying entirely within the tip Mach cone. In this method, the first order terms constitute the familiar, linearized Prandtl-Glauert approximation. The method is one of iteration. Here the second approximation is computed and plotted for a family of arrow-head wings having various leading-edge angles and thicknesses, and flying at various Mach numbers. It is necessary to use Lighthill's method to determine the strength of the attached conical shock.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1950
Accession Number
ADA076029

Entities

People

  • H. S. Tan

Organizations

  • Cornell University College of Engineering

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Air Force
  • Bodies
  • Computational Science
  • Differential Equations
  • Equations
  • Equations Of Motion
  • Flow
  • Free Stream
  • Leading Edges
  • Mach Number
  • Molecular Dynamics
  • Perturbations
  • Shock Waves
  • Two Dimensional
  • Two Dimensional Flow
  • Wave Equations

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow