Abstract:

The steady and unsteady wind tunnel test was carried out about BJ 1 aircraft and the aerodynamic characteristic was analyzed. According to the results of the tests, the unsteady aerodynamic was calculated at arbitrary angles of the tailplane and pitching frequency using the method of a data base model. On the basis of the mathematical model, the dynamic derivative of the aircraft at the different angles of the tailplane was analyzed using the technique of dynamic derivative simulation. It showed that the angle of the tailplane affected the angles of attack corresponding to the zero damping severely.

Key words: tailplane, lar ge am plitude, mat hemat ical model, dy namic der iv ativ e, unst eady wind tunnel test