期刊文献+

共轴刚性旋翼气动干扰数值计算方法 被引量:5

Numerical Method of Coaxial Rigid Rotor Aerodynamic Interaction
下载PDF
导出
摘要 建立了一个适用于共轴刚性旋翼气动特性分析的数值模拟方法。该方法采用任意拉格朗日欧拉方法(Arbitrary Lagrange Euler,ALE)描述的可压缩Navier-Stokes(N-S)方程求解流场,采用低数值耗散的Roe格式进行空间离散;使用多重嵌套网格方法以模拟双旋翼的运动。针对共轴刚性旋翼配平,引入"差量修正"策略解决了传统配平中雅克比矩阵计算复杂的问题。首先,对Harrington-2共轴双旋翼的悬停气动性能进行了计算,然后,对某2 m直径共轴双旋翼的悬停及前飞状态进行了计算,并与试验值进行了对比。结果表明:在典型状态下拉力系数的计算结果与试验值误差在3%以内,扭矩系数的计算结果与试验值误差基本在5%以内;所采用的数值计算方法对旋翼涡尾迹特征具有较高的捕捉精度,可以有效模拟共轴刚性旋翼悬停和小速度前飞下的复杂流场及其细节特征。 A numerical method is developed to predict the aerodynamic characteristics of rigid coaxial rotor. The method uses the compressible Navier.Stokes(N-S) equation described by arbitrary Lagrange Euler (ALE) to solve the flow field. A low numerical dissipative Roe format for spatial dispersion is adopted. Multiple overset grid method is used to simulate the motion of the coaxial rotor. A delta trim method is implemented to simplify the calculation of Jacobin matrix for rigid coaxial rotor trim. First,the aerodynamic performance of the Harrington-2 coaxial rotor in hover is calculated. Then,the hover and forward flight states of a 2 m diameter coaxial rotor are calculated and compared with the experimental values. The results show that,the error of the calculation result and the test value is less than 3% under the typical state,and the error of the torque coefficient is less than 5%. The numerical method has a high capture precision for the vortex wake characteristics of the rigid coaxial rotor,and can effectively simulate the detailed characteristics of the complex flow fluid in hover and the low.speed forward flight states.
作者 吴希明 祁浩天 马率 史勇杰 徐国华 WU Ximing;QI Haotian;MA Shuai;SHI Yongjie;XU Guohua(Aviation Industry Corporation of China,Ltd.,Beijing,100028,China;National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,Nanjing University of Aeronautics & Astronautics,Nanjing,210016,China;China Aerodynamics Research and Development Center,Mianyang,621000,China)
出处 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2019年第2期147-153,共7页 Journal of Nanjing University of Aeronautics & Astronautics
关键词 共轴刚性旋翼 气动干扰 数值方法 NAVIER-STOKES方程 嵌套网格 rigid coaxial rotor aerodynamic interaction numerical method Navier.Stokes equations overset mesh
  • 引文网络
  • 相关文献

参考文献5

二级参考文献47

  • 1李春华,徐国华.悬停和前飞状态倾转旋翼机的旋翼自由尾迹计算方法[J].空气动力学学报,2005,23(2):152-156. 被引量:34
  • 2许和勇,叶正寅,王刚,史爱明.基于非结构嵌套网格的旋翼前飞流场计算[J].西北工业大学学报,2006,24(6):763-767. 被引量:19
  • 3许和勇,叶正寅,王刚,史爱明.聚合多重网格法在旋翼前飞流场计算中的应用[J].航空动力学报,2007,22(2):251-256. 被引量:9
  • 4帕坦卡SV.传热与流体流动的数值计算[M].北京:科学出版社,1984..
  • 5王适存.共轴式直升机的双旋翼气动干扰问题[A]..第十一届全国直升机年会论文集[C].山东威海,1995..
  • 6约翰逊w著 孙如林译.直升机理论[M].北京:航空工业出版社,1986..
  • 7Coleman C P. A survey of theoretical and experimental coaxial rotor aerodynamic research[C]//The 19th European Rotorcraft Forum. Cernobbio, Italy: [s. n.],1993 : 14-16.
  • 8Satio S, Azuma A. A numerical approach to coaxial rotor aerodynamics[J] ,Vertica, 1982,6 : 253-266.
  • 9Andrew M J, Coaxial rotor aerodynamics in hover[J]. Vetica, 1981,5:163-172.
  • 10Akimov A I, Butov V P, Bourtsev B N,et al. Flight investigation of coaxial rotor tip vortex structure[C] // The 50th Annual Forum of the AHS. Washington, D C:AHS,1994:11-13.

共引文献60

同被引文献31

引证文献5

二级引证文献9

;
使用帮助 返回顶部