# Numerical Study on Dynamic-Stall Characteristics of Finite Wing and Rotor
## 4 Conclusions  
In this study, the unsteady CFD method was employed to simulate the dynamic-stall characteristics of a finite wing and rotor. Results can be summarized as:  
(1) The LEV of the finite wing would be restricted near the wing tip and wing root due to the influence of the wing-tip vortex. As a result, the dynamic stall of the finite wing is alleviated near the wing tip and wing root. (2) Spanwise flow would cause LEV accumulation along the wing. Therefore, the dynamic stall of the finite wing is alleviated near the wing root and aggravated near the wing tip. Figure 17: Schematic of Coriolis force on airflow near blade surface. (3) For the rotor blade, boundary-layer separation is delayed by the effect of the Coriolis force and spanwise flow. As a result, dynamic-stall characteristics are restricted. This result could be used to guide rotor-airfoil shape design in the future research. For research articles with several authors, a short paragraph specifying their individual contributions must be provided. The following statements should be used \"Conceptualization, Qing Wang, and Q.Z. ; Methodology, Q.W. ; Software, Q.W. ; Validation, Q.W. ; Formal Analysis, Q.W. ; Investigation, Q.W. Resources, Q.W. ; Data Curation, Q.W. ; Writing-Original Draft Preparation, Q.W. ; Writing-Review and Editing, Q.W. ; Visualization, Q.W. ; Supervision, Q.Z. ; Project Administration, Q.Z. The authors  
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