Low-Speed Pressure Distribution Measurements Over the Aft-Fuselage, Fins and Stabilators of a 1/9th Scale F/A-18 Wind-Tunnel Model

Abstract

The steady-state aerodynamic pressure distribution over the aft fuselage, fin and stabilator of a 119th scale FIA-18 model has been measured for varying conditions at low speeds. Pressure distributions are presented in the form of a parametric study and the integration of the pressures to obtain total loads is included to indicate the overall effects of angle of attack, sideslip, stabilator deflection and the LEX fence. The results from these wind tunnel tests have illustrated the degree to which vortical flow dominates the conditions over the aft end of the aircraft, due to the presence of the primary LEX vortex and to local separations from sharp edged surfaces.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1993
Accession Number
ADA274870

Entities

People

  • H. A. Quick
  • L. D. Maclaren

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Computational Fluid Dynamics
  • Control Surfaces
  • Flow Visualization
  • Fluid Dynamics
  • Geometry
  • Leading Edge Flaps
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Research Facilities
  • Test Facilities
  • Three Dimensional
  • Visualizations
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.