ESTIMATION OF AERODYNAMIC FORCES AND MOMENTS DERIVATIVES WITH RESPECT TO THE ANGULAR VELOCITY COMPONENTS OF THE AIRCRAFT MODEL IN A WIDE RANGE OF ANGLES OF ATTACK

摘要

Elementary estimations of derivatives of aerodynamic forces and moments coefficients with respect to the angular velocity components are presented based on the experiments on a test bed performing the aircraft model rotation at a constant angular velocity collinear to the wind tunnel incoming flow velocity vector. Analytical and semiempirical relations are given for assessing the contribution of individual elements of aircraft model to rotary derivatives. An example of determining the rotary derivatives at low flow velocities for passenger aircraft model at both small and large supercritical angles of attack is shown.