Shock-induced separation is a common aerodynamic interference problem in aerodynamics, so it is of great significance to accurately predict and control the formation and development of shock-induced separation. The numerical simulation of axisymmetric transonic bump is carried out with different turbulence models and modified forms in the unstructured hybrid grid flow software named FlowStar. Compared with computational result of commercial software and experimental data, the prediction accuracy of FlowStar in the axisymmetric transonic bump study is analyzed. The results show that variations of limiter parameter has little influence on the prediction accuracy of FlowStar in the axisymmetric transonic bump case. And the correction for turbulence models are helpful to improve the prediction accuracy of pressure distribution for both FlowStar software, while the improvement for prediction accuracy of velocity distribution varies by region. SA model and SST model have their own advantages. SST model is better in predicting pressure distribution, while SA model is better in predicting velocity distribution.