1957•NASA STI Repository (National Aeronautics and Space Administration)Requires access
A Wind-tunnel Investigation of the Low-amplitude Damping in Yaw and Directional Stability of a Fuselage-tail Configuration at Mach Numbers up to 1.10
William E. Palmer
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Abstract
Report presenting a low-amplitude free-oscillation investigation at zero angle of attack of the damping in yaw and directional stability of a fuselage-tail configuration through a range of reduced frequency. The damping in yaw was found to decrease with Mach numbers above 0.8 and became the lowest at about 1.0. An increase in reduced frequency was observed to cause a decrease in damping in yaw and directional stability for the test frequency range.