Analysis of the Linear Pitching and Yawing Motion of Curved-Finned Missiles

Abstract

Maple-Synge theory is used to establish the analytical form of the aerodynamic forces and moments acting on a four-finned, curved-finned vehicle. The linearized equations of motion are solved, and the effects of the curved- finned aerodynamics on the stability of motion are investigated. It is shown that small and moderate values of yawing moment due to angle-of-attack, characteristic of curved-finned configurations, can have significant effects on both transient and steady-state stability.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1973
Accession Number
AD0771352

Entities

People

  • Frank L. Stevens

Organizations

  • Naval Surface Warfare Center Dahlgren Division

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Forces
  • Air Launched
  • Angular Motion
  • Coefficients
  • Dynamic Pressure
  • Equations Of Motion
  • Flight
  • Frequency
  • Mach Number
  • Molecular Dynamics
  • Orientation (Direction)
  • Precession
  • Simulations
  • Steady State
  • Transverse
  • Vehicles

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Control Systems Engineering.