Lift of Finite Swept Wings with Supersonic Leading Edges

Abstract

The lift coefficient and center of pressure of swept finite wings are calculated. The product, A beta, the aspect ratio times the Mach parameter and the ratio, k/beta, the tangent of the sweep angle divided by the Mach parameter, are the determining variables of the problem. Center of pressure and life coefficient have been plotted against k/beta for various values of A beta.

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Document Details

Document Type
Technical Report
Publication Date
Jan 20, 1948
Accession Number
AD0659120

Entities

People

  • J. M. Gwinn

Organizations

  • Calspan

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Abstracts
  • Aeronautical Laboratories
  • Aircraft Wings
  • Airfoils
  • Airframes
  • Aspect Ratio
  • Boundaries
  • Buildings And Structures
  • Coefficients
  • Leading Edges
  • Mechanical Structure
  • New York
  • Pressure Distribution
  • Swept Wings
  • Thin Wings
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Nuclear and Radiation Engineering.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flight