Abstract: To study the dynamic stability derivatives of aircraft with CFD technology, an unsteady method for calculating pitching dynamic stability derivative and rolling damp dynamic derivative is developed by using small amplitude oscillation model and differential model, and a quasi-steady method is also built to calculate rolling damp dynamic derivative; the unsteady method is based on sliding mesh technique while the quasi-steady method on both sliding mesh technique and moving reference frame model; compared to the dynamic mesh used before, the sliding mesh technique can improve the computational precision as it avoids the effect of mesh deformation. The finner missile is taken as example to calculate the dynamic derivatives. The errors of two unsteady methods to calculate longitudinal combined derivatives are 0.65% and 6.13% respectively, while errors to lateral combined derivatives are 2.5% and 0.06%, and the error of quasi-steady method to obtain lateral combined derivative is 2.67%. The research shows the calculation result is consistent with the experimental data, although the quasi-steady method is less accurate than the unsteady one, nevertheless it can get result more quickly. Moreover, both the methods can be used for supersonic, subsonic and transonic dynamic derivative calculation.