Numerical simulation for flow field of helicopters based on WENO-piecewise linear scheme
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摘要: 发展了一套适合于格心格式求解器的基于加权本质无振荡(WENO)-分段线性格式的旋翼/机身气动干扰高精度CFD计算方法。应用该方法对多种旋翼/机身组合模型前飞算例进行了数值模拟,计算得到的机身表面压力系数分布与实验结果吻合良好,说明了该方法对旋翼/机身气动干扰研究的有效性。之后进一步将该方法应用到悬停状态的X3构型复合式高速直升机旋翼/机翼/螺旋桨组合模型的复杂流场模拟中,并与悬停状态孤立旋翼和旋翼/机翼组合模型的流场进行了对比。研究发现:机翼对旋翼下洗流起阻滞作用,引起机翼下方不规则流动,且螺旋桨滑流与旋翼下洗流会相互干扰产生一定的偏折,旋翼下洗流速度更大,螺旋桨滑流会产生明显的向下偏折。
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关键词:
- 飞行器设计 /
- 旋翼/机身干扰 /
- 旋翼/机翼/螺旋桨干扰 /
- 非结构网格 /
- 通量差分裂方法
Abstract: A high-precision CFD method based on WENO(weighted essentially non-oscillatory)-piecewise linear scheme was established for numerical simulation on the rotor/fuselage aerodynamics interaction flow field. And it was suitable for the CFD solver of cell-centered scheme. The pressure coefficient on the surface of the fuselage of different rotor/fuselage model examples in forward flight was calculated by the method, and the calculation results were in good agreement with the experimental results, verifying the effectiveness of the calculation method. Then, the method was extended to simulate the flow field of X3 compound high-speed helicopter rotor/wing/propeller model in hover, and the flow field was compared with flow field of single rotor and rotor/wing model in hover. The results showed that the wing acted as a retarder on the downwash of rotor, causing the irregular flow under the wing. Furthermore, the slipstream of propeller and the downwash of rotor interfered with each other to produce a certain deflection, and the speed of downwash was faster than the speed of slipstream, the downward deflection of propeller slipstream was significant. -
[1] LORBER P F,EGOLF T A.An unsteady helicopter rotor-fuselage aerodynamic interaction analysis[J].Journal of the American Helicopter Society,1990,35(3):32-42. [2] QUACKENBUSH T R,LAM C M G,BLISS D B.Vortex method for the computational analysis of rotor/body interaction[C]∥Washington,US:the 48th Annual Forum of the American Helicopter Society.Vertical Flight Society,1992:14-24. [3] RAJAGOPALAN R G,MATHUR S R.Three dimensional analysis of a rotor in forward flight[R].Buffalo,US:the 47th Annual Forum of the American Helicopter Society,1991. [4] PARK Y M,NAM H J,KWON O J.Simulation of unsteady rotor-fuselage interactions using unstructured adaptive meshes[R].Phoenix,US:the 59th Annual Forum of American Helicopter Society,2006. [5] TANABE Y,SAITO S,OTANI I.Validation of computational results of rotor fuselage interaction analysis using rflow3d code[R].Japan Aerospace Exploration Agency,AXA-RR-10-001E,2010. [6] 王博.基于CFD方法的直升机旋翼/机身流场模拟及分析[D].南京:南京航空航天大学,2007. WANG Bo.Numerical simulation and analysis of helicopter rotor/fuselage flowfield based on CFD method[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese) [7] 谢冠一.直升机旋翼/机身/尾面气动干扰特性的CFD分析[D].南京:南京航空航天大学,2012. XIE Guanyi.Analysis on aerodynamic interactions of helicopter rotor/fuselage/empennage based on CFD[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese) [8] 田书玲.基于非结构网格方法的重叠网格算法研究[D].南京:南京航空航天大学,2008. TIAN Shuling.Investigation of overset unstructured grids algorithm[D].Nanjing:Nanjing University of aeronautics and Astronautics,2008.(in Chinese) [9] 叶靓.基于非结构网格的直升机旋翼流场及噪声研究[D].南京:南京航空航天大学,2009. YE Liang.Research on the flowfield and noise of helicopter rotors based on unstructured mesh[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2009.(in Chinese) [10] 黎鑫.双拉力螺旋桨构型复合式高速直升机干扰流场的数值模拟[D].南京:南京航空航天大学,2017. LI Xin.Numerical simulation on the interaction flow field of compound double-thrust-propeller high-speed helicopters[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2017.(in Chinese) [11] ROE P L.Approximate Riemann solvers parameter vectors,and difference schemes[J].Journal of Computational Physics,1981,43(2):357-372. [12] 招启军,徐国华.直升机计算流体动力学基础[M].北京:科学出版社,2016:120-128. [13] 招启军,徐国华.使用高阶逆风通量差分裂格式的悬停旋翼流场数值模拟[J].航空动力学报,2005,20(2):186-191. ZHAO Qijun,XU Guohua.Numerical simulations for the flowfield of helicopter rotors in hovering based on high-order upwind flux-difference splitting scheme[J].Journal of Aerospace Power,2005,20(2):186-191.(in Chinese) [14] 赵国庆,招启军,吴琪.旋翼非定常气动特性CFD模拟的通用运动嵌套网格方法[J].航空动力学报,2015,30(3):546-554. ZHAO Guoqing,ZHAO Qijun,WU Qi.A universal moving-embedded grid method for CFD simulation of unsteady aerodynamic characteristics of rotor[J].Journal of Aerospace Power,2015,30(3):546-554.(in Chinese) [15] HARTEN A,HYMAN J M.Self adjusting grid methods for one-dimensional hyperbolic conservation laws[J].Journal of Computational Physics,1983,50(2):235-269. [16] SHEN Y Q,ZHA G C.A Robust seventh-order WENO Scheme and its applications[R].AIAA 2008-0757,2008. [17] VENKATAKRISHNAN V.Convergence to steady state solutions of the Euler equations on unstructured grids with limiters[J].Journal of Computational Physics,1995,118(1):120-130. [18] BLAZEK J.Computational fluid dynamics:principles and applications(second edition)[M].London:Elsevier,2005:1-4. [19] JAMESON A,TURKEL E.Implicit schemes and LU decompositions[J].Mathematics of Computation,1981,37(156):385-397. [20] BRAND A G,MCMAHON H M,KOMERATH N M.Surface pressure measurements on a body subject to vortex wake interaction[J].AIAA Journal,1989,27(5):569-574. [21] RUFFIN S M,O’BRIEN D,SMITH M J,et al.Comparison of rotor-airframe interaction utilizing overset and unstructured grid techniques[R].AIAA 2004-0046,2004. [22] FREEMAN C E,MINECK R E.Fuselage surface pressure measurements of a helicopter wind-tunnel model with a 3.15-meter diameter single rotor[R].NASA Technical Memorandum,N79-26015,1979.
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