| 涵道尾桨气动特性及翼型CFD分析 |
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| 引用本文： | 曹义华,陈科,王健,尹万力.涵道尾桨气动特性及翼型CFD分析[J].航空动力学报,2004,19(6):792-797. |
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| 作者姓名： | 曹义华 陈科 王健 尹万力 |
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| 作者单位： | 1. 北京航空航天大学,航空科学与工程学院,北京,100083
2. 陆航研究所,北京,101114 |
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| 摘 要： | 以Jameson/TVD混合格式对低速时的OAF和NACA63a312翼型的升阻特性进行了计算。该方法的特点是采用有限体积法进行离散,并用龙格-库塔时间推进法进行求解。通过将计算的结果与NASA公布的试验曲线进行对比,验证了该混合格式用于旋翼气动力计算的可行性。为了进一步研究旋翼的拉力和功率,本文建立了以微圆环动量理论和叶素理论为基础的计算模型,并用该模型计算了涵道尾桨在不同条件下的拉力和功率情况,计算的结果具有一定的代表性。
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| 关 键 词： | 航空、航天推进系统 旋翼空气动力学 TVD格式 微圆环动量理论 叶素理论 涵道尾桨 |
| 文章编号： | 1000-8055(2004)06-0792-06 |
| 收稿时间： | 2003/12/5 0:00:00 |
| 修稿时间： | 2003年12月5日 |
CFD Analysis of Aerodynamic Characteristics for the Ducted Tail Rotor and Its Aerofoil |
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| CAO Yi-hu,CHEN Ke,WANG Jian and YIN Wan-li.CFD Analysis of Aerodynamic Characteristics for the Ducted Tail Rotor and Its Aerofoil[J].Journal of Aerospace Power,2004,19(6):792-797. |
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| Authors: | CAO Yi-hu CHEN Ke WANG Jian and YIN Wan-li |
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| Institution: | School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing100083,China;School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing100083,China |
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| Abstract: | Calculation of lift-drag characteristics of OAF and NACA63a312 airfoil at low speed using Jameson/TVD mixed scheme was carried out.The feature of the method is that finite volume approach was used for numerical approximation and Runge-Kutta time-stepping advance was used to solve the Euler/Navier-Stokes equations.Comparing the numerical results with the published NASA's experimental results, it proves that the method developed here is suitable for the calculation of the rotor aerodynamics.Furthermore,a model based on circular tiny momentum theory and blade element theory is established for the study of thrust and power of the rotor under different conditions.The results of computation validate the feasibility of this model. |
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| Keywords: | aerospace propulsion system rotor aerodynamics TVD scheme circular tiny momentum theory blade element theory ducted tail rotor |
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