Flow Field on the Lee Side of a Delta Wing

Abstract

A procedure is developed which utilizes the method of characteristics to solve a portion of the flow field on the lee side of a flat plate delta wing with supersonic leading edges at angle of attack but at zero yaw. The procedure requires input conditions of a free stream Mach number an angle of attack and a sweep angle. The procedure is applied to three sets of input conditions and the resulting data are compared to published experimental and analytical data for the same set of input conditions. The comparisons indicate that the procedure may be useful in predicting the flow field in the pseudo-elliptic region and the position of the internal shock wave on the lee side of the wing.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1971
Accession Number
AD0753389

Entities

People

  • Robert G. Christophel

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Coordinate Systems
  • Data Sets
  • Delta Wings
  • Engineering
  • Equations
  • Flow Fields
  • Free Stream
  • Leading Edges
  • Mach Number
  • Method Of Characteristics
  • Numerical Analysis
  • Shock
  • Shock Waves
  • Universities
  • War Colleges
  • Waves

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.

Technology Areas

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