Abstract: Streamline curvature and strong stress effects in boundary layer appear when projectile undergoes system rotation. Corrected turbulence models(SARC, SSTRC) and original turbulence models (SA, SST) based on time dependent Reynolds average Naiver-Stokes(RANS) are used to simulate the flow field around a spinning projectile. The maximum dispersion of dynamic derivatives from corrected and original turbulence models is less than 6%, both having a good agreement with the AEDC experiment data and ARL computational data. Four estimation methods are used to verify the applicability for wing-body combination profile, and the comparison shows that satisfactory results are not obtained by the estimation methods. Symmetric distortion of circumferential surface pressure is the fundamental reason for the coincidence between corrected and original turbulence models. The separation zones computed by corrected turbulence models are larger. The inhibition strength for flow separation indicates that original turbulence models are better than corrected models.