Abstract
The development and application of a mathematical model for predicting sideslip during flight without a tail rotor are described in this paper. This method of analysis can he used to properly size a fin which will have sufficient static and dynamic stability to provide “fly‐back” capability if the tail rotor is lost, is damaged, or fails. It is well suited for preliminary design since it requires only a limited knowledge of the aerodynamic characteristics of the helicopter airframe. Sample calculations are shown for a modern attack helicopter.
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