Semi-empirical modeling of fuselage–rotor interference for comprehensive codes: influence of angle of attack

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• 作者：Berend G. van der Wall ; Jianping Yin
• 关键词：Bo105 ; Fuselage–rotor interference ; Comprehensive code ; Rotor dynamics ; Rotor aerodynamics ; Rotor trim
• 刊名：CEAS Aeronautical Journal
• 出版年：2015
• 出版时间：December 2015
• 年：2015
• 卷：6
• 期：4
• 页码：557-574
• 全文大小：3,393 KB
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• 作者单位：Berend G. van der Wall (1)
  Jianping Yin (2)
  
  1. German Aerospace Center (DLR), Institute of Flight Systems, Lilienthalplatz 7, 38108, Braunschweig, Germany
  2. German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Lilienthalplatz 7, 38108, Braunschweig, Germany
  
• 刊物主题：Aerospace Technology and Astronautics;
• 出版者：Springer Vienna
• ISSN：1869-5590

文摘

The flow field around the isolated Bo105 fuselage including the tail boom and empennage is computed by an unsteady panel code. Velocities normal to the rotor rotational plane are extracted in a volume around the rotor as a data base. A simple semi-empirical analytical formulation of the fuselage-induced velocities, based on parameter estimation from the panel code data, is extended to include rotor shaft angles of attack from \(\alpha =-90^{\circ }\) (hover, vertical climb) to +90° (vertical descent) for use in comprehensive rotor codes. This model allows the computation of fuselage–rotor interferences on the rotor blade element level in a simplified form, thus eliminating the need for costly CFD computation (of this effect). It also allows the prediction of the rotor wake geometry deformation due to the presence of the fuselage in both prescribed wake and free-wake codes. Its impact on rotor thrust, power and trim is estimated analytically using blade element momentum theory. Keywords Bo105 Fuselage–rotor interference Comprehensive code Rotor dynamics Rotor aerodynamics Rotor trim