UNSTEADY AERODYNAMICS FOR ADVANCED CONFIGURATIONS. PART 2. A TRANSONIC BOX METHOD FOR PLANAR LIFTING SURFACES

Abstract

The fundamental equations of the transonic box method were derived, based on the representation of the velocity potential by a doublet distribution. They form the basis of a systematic method of treating an oscillating wing at M = 1, analogous to the supersonic Mach box method. A digital computer program, written in Fortran IV, is presented. The program applies to a planar wing of polygonal planform, with a straight trailing edge, and as many as three sweep angles along the leading edge. For a maximum of ten modes of oscillation, the program computes the oscillatory potentials and pressures and a generalized force matrix. Results obtained from the program are compared with existing theoretical and experimental values. Several possible extensions of the method are described.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1965
Accession Number
AD0618097

Entities

People

  • E. R. Rodemich
  • L. V. Andrew

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aspect Ratio
  • Boundaries
  • Boundary Value Problems
  • Computer Programs
  • Computers
  • Coordinate Systems
  • Delta Wings
  • Differential Equations
  • Equations
  • Leading Edges
  • Mach Number
  • Planform
  • Pressure Distribution
  • Shape
  • Trailing Edges
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow