Stability Derivatives of Triangular Wings at Supersonic Speeds

Abstract

The analysis of the stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds, given in NACA TN No. l423, is extended to apply to triangular wings having large vertex angles and traveling at supersonic speeds. The lift, rolling moment due to siderlip, and damping in roll and pitch for this more general case have been treated elsewhere on the basis of the theory of small disturbances.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1948
Accession Number
ADA380737

Entities

People

  • Frank S. Malvestuto Jr.
  • Herbert S. Ribner

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • C4I

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aspect Ratio
  • Cartesian Coordinates
  • Center Of Gravity
  • Coefficients
  • Delta Wings
  • Differential Equations
  • Equations
  • Flight
  • Flight Speeds
  • Leading Edges
  • Mach Number
  • Partial Differential Equations
  • Pressure Distribution
  • Steady State
  • Wave Equations
  • Yaw

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow