Abstract
In order to determine the rotary derivatives of forces and moments with respect to the angular velocity components, a method of their estimation is developed based on calculations of distributed static aerodynamic characteristics of aircraft under the assumption of smallness of its angular motion perturbations. To estimate the derivatives with respect to the transverse component of the angular velocity, calculations by discrete vortex method are additionally used. Examples of estimates for the passenger aircraft model in a wide range of angles of attack are given.
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