Abstract
The dynamic stability derivative is the key parameter of the aircraft control system and the boundary analysis of the dynamic stability criterion. The accurate evaluation of dynamic derivative is of great importance to the design and flight of the aircraft. A method to predict the derivative of pitch damping is presented. The unsteady aerodynamic force is obtained by solving the unsteady flow field, and the static and dynamic derivatives of the aircraft are obtained by using integral method and least square method. By comparing the aerodynamic derivatives at different equilibrium positions and different centers of gravity, it can be seen that the calculated results are in good agreement with the experiment. It indicates that the present method has satisfactory order and efficiency and be suitable for engineering problems.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
