Flow Visualization of the effect of Pitch Rate on the Vortex Development on the Scale Model of a F-18 Fighter Aircraft

Abstract

Experiments were performed in a water tunnel to visualize the vortex bursting phenomenon on a 1/48th scale model of the F-18 fighter aircraft. Photographs were taken to investigate the effect of pitch rate and yawing on bursting locations of vortices shed from the forebody and the strake during simple pitch up and simple pitch down maneuvers in an angle of attack range up to 50 degrees. It was found that the vortex burst point moves upstream with increasing pitch rate. At the same pitch rate, vortex bursting was usually found to occur earlier for the pitch-down than for the pitch-up maneuver. Aircraft yawing generated significant vortex asymmetries due to earlier vortex bursting on the windward side thus leading to undesireable side forces and yawing moments. Keywords: Fluid dynamics; Aerodynamics. (KT)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1989
Accession Number
ADA214244

Entities

People

  • Sung-nam Park

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Computational Fluid Dynamics
  • Fighter Aircraft
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Fluid Mechanics
  • Geometry
  • Hydrodynamics
  • Personnel Management
  • Photographs
  • Photography
  • Scale Models
  • Three Dimensional
  • Water Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.