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.

Calculation Methods for Estimating the Rotary Derivatives of Forces and Moments Acting on the Aircraft

In order to clarify the results of experimental studies with free-spinning aircraft models in a vertical wind tunnel, the analysis of the force pitching moment coefficients acting on the model, full-scale aircraft and their elements was carried out. It is shown that some differences in these coefficients are acceptable, which is confirmed by a satisfactory convergence of the results of model studies and full-scale aircraft flight tests.

To the Estimation of Force and Pitching Moment Coefficients Acting on the Model, Full-Scale Aircraft and Their Elements at Supercritical Angles of Attack and in a Spin

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

Miroslav Sergeevich Makhnev

Papers

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

Determination and analysis of roll and yaw rotary derivatives of wig vehicle using numerical simulation