A Wing Rock Model for the F-14A Aircraft

Abstract

An investigation of inertial coupling and its contribution to wing rock in the F-14A aircraft has been conducted. Wind tunnel data was used to obtain the stability parameters for angles of attack from zero to 25 degrees, after which linear and nonlinear analyses of the equations of motion were completed. The linearized analysis of the uncoupled longitudinal and lateral- directional equations was included to provide a baseline for comparison with the fully coupled, nonlinear equations. In both cases, the equations of motion were solved numerically and time history traces produced to illustrate aircraft response. Results indicate that a stable short period mode can feed damping energy into an unstable dutch roll mode via the coupling of the equations to produce a stable limit cycle very similar to those experienced in the aircraft. Numerous suggestions for follow on research are presented.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1992
Accession Number
ADA243109

Entities

People

  • Steven R. Wright

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Computational Science
  • Computer Programs
  • Computers
  • Control Surfaces
  • Databases
  • Differential Equations
  • Dynamic Response
  • Flight
  • Geometry
  • Linear Systems
  • Mach Number
  • Mechanics
  • Numerical Analysis
  • Numerical Integration
  • Research Facilities
  • Resonant Frequency

Readers

  • Aerodynamics/Aeronautics.
  • Structural Dynamics.