New Systematic CFD Methods to Calculate Static and Single Dynamic Stability Derivatives of Aircraft

Table 5

Rotary derivative results.

Angle of attack (degree)	Unsteady at time of step motion with constant	Unsteady at time of step motion with constant	Calculation; results	Wind tunnel; testing [18]
0; 5; 10; 15	0.00081; 0.012704; 0.02255; 0.03806	0.012749; 0.0249; 0.04125; 0.05326	−1.19425; −1.2196; −1.87; −1.52	Not given; Not given; −1.75; −1.5