Theoretical Loading at Supersonic Speeds of Flat Swept-Back Wings with Interacting Trailing and Leading Edges

Abstract

By the method of superposition of conical flows, the load distribution is calculated for regions of a long, rectilinear, swept-back wing behind the points at which the Mach lines from the trailing-edge apex intersect the leading edge. It is found that a good approximation to the load can be obtained by the application of a fairly simple correction factor to the two-dimensional subsonic distribution. The similarity to two-dimensional flow is used to derive expressions for the loss of lift behind the Mach lines from the tips of the wing.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1949
Accession Number
ADA380520

Entities

People

  • Doris Cohen

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Agreements
  • Aspect Ratio
  • Boundaries
  • Cancellation
  • Delta Wings
  • Dynamic Pressure
  • Flow
  • Leading Edges
  • Load Distribution
  • Mach Number
  • Pressure Distribution
  • Sweptback Wings
  • Trailing Edges
  • Two Dimensional
  • Two Dimensional Flow
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis

Technology Areas

  • Hypersonics