Graphical Method of Obtaining Theoretical Lift Distributions on Thin Wings at Supersonic Speeds

Abstract

A graphical method is presented for calculating the linearized lift distribution on thin wings at supersonic speeds. The technique may be applied to all wing regions except those influenced by interacting flow fields off the wing-plan boundaries. The lifting-pressure coefficients are obtained as the sum of a graphical line integration and several terms that are functions of only the plan form. Pressure coefficients obtained by the graphical method for a swept trapezoidal wing and for a wing with straight-swept leading edge and parabolic wing-tip are compared with those derived by closed-form integration. The lift distributions for two plan forms previously unsolved are also included.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1948
Accession Number
ADA381050

Entities

People

  • Clarence B. Cohen
  • John C. Evvard

Organizations

  • Glenn Research Center

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Accuracy
  • Boundaries
  • Cartesian Coordinates
  • Coordinate Systems
  • Curvature
  • Flow
  • Flow Fields
  • Free Stream
  • Geometry
  • Grids
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Thin Wings
  • Trailing Edges
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Approximation Theory.

Technology Areas

  • Hypersonics