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Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Fighter Model Employing a Low-aspect-ratio Unswept Wing and a Horizontal Tail Mounted Well above the Wing Plane - Lateral and Directional StabilityThe static lateral- and directional-stability characteristics of a high-speed fighter-type airplane, obtained from wind-tunnel tests of a model, are presented. The model consisted of a thin, unswept wing of aspect ratio 2.3 and taper ratio 0.385, a body, and a horizontal tail mounted in a high position on a vertical tail. Rolling-moment, yawing moment, and cross-wind-force coefficients are presented for a range of sideslip angles of -5 deg. to +5 deg, for Mach numbers of 0.90, 1.45, and 1.90. Data are presented which show the effects on the lateral and directional stability of: (1) component parts of the complete model, (2) modification of the empennage so as to provide different heights of the horizontal tail above the wing plane, (3) angle of attack, and (4) dihedral of the wing.
Document ID
20090025891
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Wetzel, Benton E. (National Advisory Committee for Aeronautics. Ames Aeronautical Lab. Moffett Field, CA, United States)
Date Acquired
August 24, 2013
Publication Date
August 26, 1954
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NACA-RM-SA54H26b
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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