Numerical simulation of aerodynamic interactions among helicopter rotor, fuselage, engine and body of revolution

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• 作者：YiHua Cao (1)
  ZhenLong Wu (1)
  JunSen Huang (1)
  
• 关键词：numerical simulation ; aerodynamic interaction ; helicopter ; actuator disc model ; rotating reference frame model
• 刊名：SCIENCE CHINA Technological Sciences
• 出版年：2014
• 出版时间：June 2014
• 年：2014
• 卷：57
• 期：6
• 页码：1206-1218
• 全文大小：
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• 作者单位：YiHua Cao (1)
  ZhenLong Wu (1)
  JunSen Huang (1)
  
  1. School of Aeronautic Science and Engineering, Beihang University, Beijing, 100191, China
  
• ISSN：1869-1900

文摘

Numerical simulations of helicopter aerodynamic interactions among the main rotor, fuselage, engine inlets/outlets and slung loads of specific geometries have been conducted by very few researchers. In this work, the steady-state compressible Reynolds-averaged navier-stokes equations are solved to study the aerodynamic interactions among helicopter rotor, fuselage, engine and body of revolution in three cases, namely MI-171V5, ROBIN and UH-60A. In the first case, the downwash flow provided by the rotor of the uniform actuator disc model induces a significant deflection of the airflow velocity. The vortex-shaped distribution and evolution are discussed in detail. The engine can effectively change the overall flow field. The asymmetry of the flow field is observed by using the non-uniform actuator disc model. Qualitative analysis of ROBIN and quantitative computation of UH-60A show a consistent accuracy of the rotating reference frame model for rotor. The blade tip vortex motion of UH-60A is simulated and its radial position prediction is compared to empirical formulas. While performing flow of UH-60A in hover, both the fuselage normal force and rotor lift decrease because of the impact of the body of revolution.