Aerodynamic Stability Technology for Maneuverable Missiles. Volume II. Asymmetric Vortex Effects Computer Program

Abstract

A procedure for estimating the effects of asymmetric lee-side vortices on slender missile configurations with and without tails is developed, using both theoretical and empirical inputs. A computerized model of the procedure which calculates induced side forces, yawing moments, tail forces and rolling moments is presented. Program flow charts, input instructions and sample cases are provided. Comparisons between experiments data and program calculations show acceptable preliminary design level accuracies. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1979
Accession Number
ADA068971

Entities

People

  • Gennaro F. Aiello
  • Michael C. Bateman

Organizations

  • Martin Marietta

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Bodies
  • Boundary Layer
  • Equations
  • Experimental Data
  • Fineness Ratio
  • Flow Fields
  • Fluid Flow
  • Geometry
  • High Angles
  • Leading Edges
  • Mach Number
  • Potential Flow
  • Reynolds Number
  • Slender Bodies
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computer Science.