Effects of the Installation and Operation of Jet-Exhaust Yaw Vanes on the Longitudinal and Lateral-Directional Characteristics of the F-14 Airplane

Abstract

An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine the effects of the installation and operation of jet-exhaust yaw vanes on the longitudinal and lateral-directional characteristics of the F- 14 airplane. The model was tested at Mach numbers from 0.70 to 1.25 at angles of attack from 0 deg to 4.3 deg. Compressed air was used to simulate nozzle exhaust flow from jet off up to a nozzle pressure ratio of 8. The results of the investigation show that the yaw vanes can augment the rudders to provide directional control, but further investigation will be necessary to optimize the deflection schedule associated with the various nozzle power settings. Installation of the yaw vanes also resulted in a drag penalty that will have to be considered in determining the overall benefits of the yaw vanes.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1987
Accession Number
ADA279628

Entities

People

  • Bobby L. Berrier
  • David E. Reubush

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Airplanes
  • Boundaries
  • Boundary Layer
  • Control Surfaces
  • Dynamic Pressure
  • Exhaust Nozzles
  • Flow
  • High Angles
  • High Pressure
  • Horizontal Stabilizers
  • Jet Flow
  • Mach Number
  • Pressure Distribution
  • Static Pressure
  • Strain Gages

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.