Transactions of Nanjing University of Aeronautics & Astronautics
Research on Aerodynamic Characteristics of Hovering Rotor Based on Leading Edge Droop
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Abstract:
In view of the reduction of hovering efficiency near high tension when a helicopter rotor hovers， a numerical simulation method of lifting rotor hovering aerodynamic characteristics based on leading edge droop is established in this paper. It is dominated by Reynolds average N-S equation in integral form. Firstly， VR-12 airfoil is taken as the research object， and the influence of leading edge droop angle on the aerodynamic characteristics of two-dimensional airfoil is studied. Secondly， the modified 7A rotor is taken as the research object， and the effects of different leading edge droop angles at the position of blade r/R=0.75—1 on the aerodynamic characteristics in hover are explored. It is found that the leading edge droop can significantly improve the aerodynamic characteristics of two-dimensional airfoil and three-dimensional hovering rotor near high angle of attack， and can effectively inhibit the generation of stall vortex.
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Project Supported:
This work was supported by the National Natural Science Foundation of China （No.11972190） and the Aeronautical Science Foundation of China（No.20185752）.
Clc Number:
V211.52
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