Accession Number:

ADA279628

Title:

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

Descriptive Note:

Technical paper

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s):

• Reubush, David E.
• Berrier, Bobby L.

Report Date:

1987-12-01

Pagination or Media Count:

121.0

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.

Descriptors:

• *YAW
• *JET ENGINE EXHAUST
• *JET VANES
• ANGLE OF ATTACK
• JET FIGHTERS
• MACH NUMBER
• TRANSONIC WIND TUNNELS

Subject Categories:

• Celestial Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE