变形体超临界翼型动态气动特性
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摘要
为实现飞行器外形根据来流条件变化做出相应调整,需深入了解变形体非定常气动现象和机理。以典型超临界翼型为研究对象,分别制定了翼型厚度及弯度变形方案,实现了翼型柔性变形。利用数值仿真方法在高雷诺数条件下开展了翼型厚度、弯度连续变形带来的非定常效应。结果表明,翼型厚度、弯度连续变形均会形成明显的升、阻力系数迟滞环,且频率越高、幅度越大,变形导致的非定常效应也越强;相对而言,翼型弯度变形产生的非定常效应较厚度变形产生的非定常效应更明显。最后通过分析流线图及压力系数分布图发现,流动结构随几何变形的迟滞性会导致非定常效应的产生。
People hope that aircraft shape can adjust according to the change of flow condition,thus it is essential to learn about the unsteady aerodynamic phenomenon and mechanism of deformable aircrafts.Then the deformation vehicle performance can be improved,and the safety of flight can be ensured.In this paper,supercritical airfoil was focused on,and airfoil thickness and camber deformation schemes were designed,respectively.Numerical simulation method was used to simulate the unsteady effect due to the airfoil thickness or camber deformed in high Reynolds number condition.The results show that the unsteady effect is strong with distinguishable lift and drag hysteresis loops.In addition,as the deformation frequency and amplitude increase,the unsteady effects are significantly strengthened.The unsteady effect resulted from the camber deformation is relatively stronger than that from the thickness deformation.Finally,by analysing the flow streamline and pressure coefficient distribution,the unsteady effects with geometric distortion can be produced by the hysteresis of the flow structure,such as the strength and location of shock,and the boundary layer separation.
People hope that aircraft shape can adjust according to the change of flow condition,thus it is essential to learn about the unsteady aerodynamic phenomenon and mechanism of deformable aircrafts.Then the deformation vehicle performance can be improved,and the safety of flight can be ensured.In this paper,supercritical airfoil was focused on,and airfoil thickness and camber deformation schemes were designed,respectively.Numerical simulation method was used to simulate the unsteady effect due to the airfoil thickness or camber deformed in high Reynolds number condition.The results show that the unsteady effect is strong with distinguishable lift and drag hysteresis loops.In addition,as the deformation frequency and amplitude increase,the unsteady effects are significantly strengthened.The unsteady effect resulted from the camber deformation is relatively stronger than that from the thickness deformation.Finally,by analysing the flow streamline and pressure coefficient distribution,the unsteady effects with geometric distortion can be produced by the hysteresis of the flow structure,such as the strength and location of shock,and the boundary layer separation.
引文
[1]Secanell M,Suleman A,Gamboa P.Design of a morphing airfoil for a light unmanned aerial vehicle using high-fidelity aerodynamic shape optimization[C]//Proceedings of the 46th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,2005.Austin,TX,United States:American Inst.Aeronautics and Astronautics Inc.
[2]Cui Erjie,Bai peng,Yang Jiming.Development road of smart morphing aircraft[J].Aeronautical Manufacturing Technology,2007,(8):38-41.(in Chinese)崔尔杰,白鹏,杨基明.智能变形飞行器的发展道路[J].航空制造技术,2007,(8):38-41.
[3]Florance J P,Burner A W,Fleming G A,et al.Contributions of the NASA Langley research center to the DARPA/AFRL/NASA/Northrop Grumman smart wing program[C]//Proceedings of the 44th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,2003.Norfolk,VA,United states:American Inst.Aeronautics and Astronautics Inc.
[4]Kudva J N,Martin C A,Scherer L B,et al.Overview of the DARPA/AFRL/NASA Smart Wing Program[C]//Proceedings of SPIE Conference on Industrial and Commercial Applications of Smart Structures Technologies,1999:230.
[5]Kudva J N.Overview of the DARPA smart wing project[J].Journal of Intelligent Material Systems and Structures,2004,15(4):261-267.
[6]Ajaj R M,Beaverstock C S,Friswell M I.Morphing aircraft:The need for a new design philosophy[J].Aerospace Science and Technology,2016,49:154-166.
[7]Nekoubin N,Nobari M R H.Numerical investigation of transonic flow over deformable airfoil with plunging motion[J].Applied Mathematics and Mechanics,2015,37(1):75-96.
[8]Walker W P,Patil M J.Unsteady aerodynamics of deformable thin airfoils[J].Journal of Aircraft,2014,51(6):1673-80.
[9]Gandhi F,Anusonti-Inthra P.Skin design studies for variable camber morphing airfoils[J].Smart Materials and Structures,2008,17(1):015025.
[10]Andersen P B,Gaunaa M,Bak C,et al.A dynamic stall model for airfoils with deformable trailing edges[J].Journal of Physics:Conference Series,2007,75:012028.
[11]Xu Guowu,Bai Peng,Shi Wen.Primary research of morphing scheme over 2Dairfoil[J].Chinese Quarterly of Mechanics,2011,(4):570-576.(in Chinese)徐国武,白鹏,石文.二维翼型可变形方案初步研究[J].力学季刊,2011,(4):570-6.
[12]Hao Nansong,Yang Wenchao,Yang Jiming.Experimental study of unsteady aerodynamic characteristics of variable camber wing at low Reynolds number[J].Journal of Experimental Mechanics,2014,(3):294-301.(in Chinese)郝南松,杨文超,杨基明.低Re数下变弯度机翼的非定常气动特性实验研究[J].实验力学,2014,(3):294-301.
[13]Chen Qian,Bai Peng,Li Feng.Morphing aircraft wing variablesweep:two practical methods and their aerodynamic characteristics[J].Acta Aerodynamica Sinica,2012,30(5):658-663.(in Chinese)陈钱,白鹏,李锋.可变形飞行器机翼两种变后掠方式及其气动特性机理[J].空气动力学学报,2012,30(5):658-63.
[14]Gao Yanfeng,Liu Zhifan,Wang Xiaohong.Study on the supersonic unsteady aerodynamic force for the morphing airfoil[J].Acta Aerodynamica Sinica,2014,32(1):69-76.(in Chinese)高彦峰,刘志帆,王晓宏.可变形翼型超声速非定常气动力的研究[J].空气动力学学报,2014,32(1):69-76.
[15]Gao Yanfeng,Wang Xiaohong,Liu Zhifan.Study on the subsonic unsteady aerodynamic force for the morphing joukowski airfoil[J].Chinese Quarterly of Mechanics,2012,(1):1-9.(in Chinese)高彦峰,王晓宏,刘志帆.可变形儒可夫斯基翼型亚音速非定常气动力的研究[J].力学季刊,2012,(1):1-9.
[16]Zhang Yifan,Zhang Xiaoli.Credibility analysis of RAE2822airfoil transonic flow computation[J].Aeronautical Computing Technique,2009,(4):68-70.(in Chinese)张一帆,张小莉.RAE2822翼型跨音速流动CFD计算的可信度分析[J].航空计算技术,2009,(4):68-70.
[17]Gao Yanfeng.Study on the unsteady aerodynamics characteristics for the morphing airfoil[D].University of Science and Technology of China,2012.(in Chinese)高彦峰.可变形翼型的非定常气动特性研究[D].中国科学技术大学,2012.
[18]Yang Wenchao.Experimental investigation on the flow separation behaviors of a variable camber wing[D].University of Science and Technology of China,2012.(in Chinese)杨文超.可变弯度机翼流动分离特性的实验研究[D].中国科学技术大学,2012.
[2]Cui Erjie,Bai peng,Yang Jiming.Development road of smart morphing aircraft[J].Aeronautical Manufacturing Technology,2007,(8):38-41.(in Chinese)崔尔杰,白鹏,杨基明.智能变形飞行器的发展道路[J].航空制造技术,2007,(8):38-41.
[3]Florance J P,Burner A W,Fleming G A,et al.Contributions of the NASA Langley research center to the DARPA/AFRL/NASA/Northrop Grumman smart wing program[C]//Proceedings of the 44th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,2003.Norfolk,VA,United states:American Inst.Aeronautics and Astronautics Inc.
[4]Kudva J N,Martin C A,Scherer L B,et al.Overview of the DARPA/AFRL/NASA Smart Wing Program[C]//Proceedings of SPIE Conference on Industrial and Commercial Applications of Smart Structures Technologies,1999:230.
[5]Kudva J N.Overview of the DARPA smart wing project[J].Journal of Intelligent Material Systems and Structures,2004,15(4):261-267.
[6]Ajaj R M,Beaverstock C S,Friswell M I.Morphing aircraft:The need for a new design philosophy[J].Aerospace Science and Technology,2016,49:154-166.
[7]Nekoubin N,Nobari M R H.Numerical investigation of transonic flow over deformable airfoil with plunging motion[J].Applied Mathematics and Mechanics,2015,37(1):75-96.
[8]Walker W P,Patil M J.Unsteady aerodynamics of deformable thin airfoils[J].Journal of Aircraft,2014,51(6):1673-80.
[9]Gandhi F,Anusonti-Inthra P.Skin design studies for variable camber morphing airfoils[J].Smart Materials and Structures,2008,17(1):015025.
[10]Andersen P B,Gaunaa M,Bak C,et al.A dynamic stall model for airfoils with deformable trailing edges[J].Journal of Physics:Conference Series,2007,75:012028.
[11]Xu Guowu,Bai Peng,Shi Wen.Primary research of morphing scheme over 2Dairfoil[J].Chinese Quarterly of Mechanics,2011,(4):570-576.(in Chinese)徐国武,白鹏,石文.二维翼型可变形方案初步研究[J].力学季刊,2011,(4):570-6.
[12]Hao Nansong,Yang Wenchao,Yang Jiming.Experimental study of unsteady aerodynamic characteristics of variable camber wing at low Reynolds number[J].Journal of Experimental Mechanics,2014,(3):294-301.(in Chinese)郝南松,杨文超,杨基明.低Re数下变弯度机翼的非定常气动特性实验研究[J].实验力学,2014,(3):294-301.
[13]Chen Qian,Bai Peng,Li Feng.Morphing aircraft wing variablesweep:two practical methods and their aerodynamic characteristics[J].Acta Aerodynamica Sinica,2012,30(5):658-663.(in Chinese)陈钱,白鹏,李锋.可变形飞行器机翼两种变后掠方式及其气动特性机理[J].空气动力学学报,2012,30(5):658-63.
[14]Gao Yanfeng,Liu Zhifan,Wang Xiaohong.Study on the supersonic unsteady aerodynamic force for the morphing airfoil[J].Acta Aerodynamica Sinica,2014,32(1):69-76.(in Chinese)高彦峰,刘志帆,王晓宏.可变形翼型超声速非定常气动力的研究[J].空气动力学学报,2014,32(1):69-76.
[15]Gao Yanfeng,Wang Xiaohong,Liu Zhifan.Study on the subsonic unsteady aerodynamic force for the morphing joukowski airfoil[J].Chinese Quarterly of Mechanics,2012,(1):1-9.(in Chinese)高彦峰,王晓宏,刘志帆.可变形儒可夫斯基翼型亚音速非定常气动力的研究[J].力学季刊,2012,(1):1-9.
[16]Zhang Yifan,Zhang Xiaoli.Credibility analysis of RAE2822airfoil transonic flow computation[J].Aeronautical Computing Technique,2009,(4):68-70.(in Chinese)张一帆,张小莉.RAE2822翼型跨音速流动CFD计算的可信度分析[J].航空计算技术,2009,(4):68-70.
[17]Gao Yanfeng.Study on the unsteady aerodynamics characteristics for the morphing airfoil[D].University of Science and Technology of China,2012.(in Chinese)高彦峰.可变形翼型的非定常气动特性研究[D].中国科学技术大学,2012.
[18]Yang Wenchao.Experimental investigation on the flow separation behaviors of a variable camber wing[D].University of Science and Technology of China,2012.(in Chinese)杨文超.可变弯度机翼流动分离特性的实验研究[D].中国科学技术大学,2012.