An aircraft steady dynamic derivatives calculation method

Dynamic derivatives prediction is essential for aircraft stability analysis, but CFD (Computational Fluid Dynamics) methods based on unsteady flow solutions require excessive time and computational resources. An aircraft steady dynamic derivatives calculation method based on the rotating reference frame technique is put forward. The rotating reference frame technique is applied to gain the pitching-moment coefficient pitch rate derivative by simulating the steady climb movement. This technique is also employed to acquire the roll and yaw rate derivatives by simulating the steady roll and yaw movement respectively. The steady dynamic derivatives of a missile with cruciform tails and a seaplane were calculated. The results agree well with experimental data, reference data and data acquired by other methods. This method could be used to calculate the steady dynamic derivatives of aircrafts with complicated configurations.