Formulas and Charts for the Supersonic Lift and Drag of Flat Swept-Back Wings With Interacting Leading and Trailing Edges

Abstract

The problem is considered of a wing with rectilinear plan form swept so that both leading and trailing edges lie within their respective Mach cones; moreover, the Mach lines from the trailing edge apex intersect the leading edge. Formulas and design charts are presented for the lift in such a case, based on approximate formulas for the lift distribution developed in NACA TN 1991, l949.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1950
Accession Number
ADA380690

Entities

People

  • Doris Cohen

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aspect Ratio
  • Boundaries
  • Cancellation
  • Cartesian Coordinates
  • Delta Wings
  • Flow
  • Flow Fields
  • Leading Edges
  • Load Distribution
  • Mach Number
  • Pressure Distribution
  • Sweptback Wings
  • Trailing Edges
  • Two Dimensional
  • Wing Tips

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics