翼型改型对超临界翼型气动性能影响的研究
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摘要
超临界翼型由于拥有良好的跨声速气动性能,而被广泛应用于民航飞机、运输机和轰炸机等高亚声速巡航飞机上。而二维翼型的设计,是三维机翼的基础,因此,设计人员在对二维超临界翼型的研究上,花费了大量精力。鉴于此,本文选取某超临界翼型,探讨改型对超临界翼型气动性能的影响。
本文采用翼型正设计方法以及计算流体力学基本原理,对NPU-S 73613翼型进行数值模拟,首先根据已公布的翼型实验数据,对原翼型进行计算,来验证软件和算法的可靠性。而后通过修改不同的翼型参数,这其中包括厚度、弯度、前缘半径、以及尾缘厚度,研究翼型气动性能的变化。最后根据前述计算结果和已有的经验,在原翼型的基础上,推出两种新的改型方案,达到改善原翼型气动性能的目的。
计算结果表明,厚度、厚度位置和发散尾缘的变化,对翼型的气动性能影响很大,特别是最大厚度位置和发散尾缘的调整,在减弱激波强度,推迟临界马赫数方面效果明显。改型1在新的设计状态下升阻比下降了2.14%;而改型2的升阻比则提高了2.67%,使原翼型在跨声速阶段气动性能有了一定的提高。
The supercritical airfoil has been widely used in high subsonic cruise aircraft, such as civil aircraft, transport aircraft and bomber aircraft, due to their good transonic aerodynamic performance. For two dimensional airfoil design, the researchers put massive effort since it is the basis of the three dimensional wing design. This thesis investigated the effect of the airfoil modification on the areodynamic performance of a certain supercritical airfoil.
Using airfoil direct problem design method, based on published airfoil test data, this work calculated the original airfoil NPU-S 73613 and verified the reliability of the software and algrithom by applying Fluent commercial software. Furthermore, this research investigated the change of the airfoil aerodynamic performance by modifying different airfoil parameters, such as thickness, camber, leading edge radius and trailing edge thickness. Lastly, this thesis proposed two new modified airfoils on the basis of the original airfoil according to previous results and experiences in order to improve the aerodynamic performance of the original airfoil.
The predicted results showed that the effect of the modification of thickness, its location and divergent trailing edge on the aerodynamic feature is dramatic. Especially the modification of the location of the maximum thickness and divergent trailing edge has significant influence on the reduction of the intensity of the shock wave and the delay of the critical March number. In comparison to the original airfoil, the lift to drag ratio for the modification 1 and 2 increased -2.14% and 2.67% respectively, which indicated the remarkable improvement of the transonic aerodynamic performance to the original airfoil.
本文采用翼型正设计方法以及计算流体力学基本原理,对NPU-S 73613翼型进行数值模拟,首先根据已公布的翼型实验数据,对原翼型进行计算,来验证软件和算法的可靠性。而后通过修改不同的翼型参数,这其中包括厚度、弯度、前缘半径、以及尾缘厚度,研究翼型气动性能的变化。最后根据前述计算结果和已有的经验,在原翼型的基础上,推出两种新的改型方案,达到改善原翼型气动性能的目的。
计算结果表明,厚度、厚度位置和发散尾缘的变化,对翼型的气动性能影响很大,特别是最大厚度位置和发散尾缘的调整,在减弱激波强度,推迟临界马赫数方面效果明显。改型1在新的设计状态下升阻比下降了2.14%;而改型2的升阻比则提高了2.67%,使原翼型在跨声速阶段气动性能有了一定的提高。
The supercritical airfoil has been widely used in high subsonic cruise aircraft, such as civil aircraft, transport aircraft and bomber aircraft, due to their good transonic aerodynamic performance. For two dimensional airfoil design, the researchers put massive effort since it is the basis of the three dimensional wing design. This thesis investigated the effect of the airfoil modification on the areodynamic performance of a certain supercritical airfoil.
Using airfoil direct problem design method, based on published airfoil test data, this work calculated the original airfoil NPU-S 73613 and verified the reliability of the software and algrithom by applying Fluent commercial software. Furthermore, this research investigated the change of the airfoil aerodynamic performance by modifying different airfoil parameters, such as thickness, camber, leading edge radius and trailing edge thickness. Lastly, this thesis proposed two new modified airfoils on the basis of the original airfoil according to previous results and experiences in order to improve the aerodynamic performance of the original airfoil.
The predicted results showed that the effect of the modification of thickness, its location and divergent trailing edge on the aerodynamic feature is dramatic. Especially the modification of the location of the maximum thickness and divergent trailing edge has significant influence on the reduction of the intensity of the shock wave and the delay of the critical March number. In comparison to the original airfoil, the lift to drag ratio for the modification 1 and 2 increased -2.14% and 2.67% respectively, which indicated the remarkable improvement of the transonic aerodynamic performance to the original airfoil.
引文
[1]李广义.国外大型军用运输机发展现状与趋势[J].航空制造技术, 2005, 9 : 36-43
[2]陈在薪,刘福长,鲍国华.空气动力学[D] .北京:航空工业出版社, 1993
[3]陶洋.实体鼓包改进超临界翼型气动特性数值计算及风洞试验研究[D] .绵阳:中国空气动力发展研究中心, 2004
[4]李亚臣,王晋军.发散后缘与Gurney襟翼对超临界翼型影响的实验研究[A].全国实验流体力学学术会议, 2005: 295-299
[5]李亚臣,王晋军,樊建超.超临界翼型Gurney襟翼增生研究[J].北京航空航天大学学报, 2003, 29(6) : 471-474
[6]阎文成.超临界翼型附面层分离及控制方案研究[D] .西安:西北工业大学, 2004
[7]阎超,谢磊,李云晓.翼型的气动最优化设计方法和反设计方法[J].空气动力学报, 1999, 17(1) : 61-67
[8]钱瑞战,乔志德,宋文萍.基于N-S方程的跨声速翼型多目标、多约束优化设计[J].空气动力学报, 2000, 18(3) : 350-353
[9]罗惕乾.流体力学[M] .北京:机械工业出版社, 2003: 267-276
[10]钱翼稷.空气动力学[M] .北京:北京航空航天大学出版社, 2004: 284-304
[11]方宝瑞.飞机气动布局设计[M] .北京:航空工业出版社, 1997: 525-547
[12]赖巍.高功率风力机叶型数值模拟及实验研究[D] .沈阳:沈阳航空工业学院, 2007
[13]夏商周.高高升力翼型数值模拟[D] .沈阳:沈阳航空工业学院, 2006
[14]章子雄,董曾男.粘性流体力学[M] .北京:清华大学出版社, 1998: 135-137
[15]李杰. Navier-Stokes方程数值模拟及湍流模型研究[D] .西安:西北工业大学, 2006
[16]王福军.计算流体动力学分析[M].北京:清华大学出版社, 2005 :120-126
[17]阎超.计算流体力学方法及应用[M] .北京:北京航空航天大学出版社, 2006: 227-228
[18]柳森.动翼型跨声速非定常粘性绕流的数值模拟[D] .西安:西北工业大学, 1993
[19]李孝伟,孙刚,乔志德.欧拉方程多段翼型绕流计算的嵌套网格方法[J].空气动力学学报, 1998, 16(4) : 492-497
[20]杨青.超临界翼型、机翼的定常和非定常流场数值模拟[D] .西安:西北工业大学, 2004
[21] Q.Xiao, H.M.Tsai, F.Liu. Numerical Study of Transonic Buffet On a Supercritical Airfoil [J]. AIAA Journal. March 2006.620-627
[22] Simon Parinchand-Ouellet, Christophe Tribes, Jean-Ynes Trepanier. Airfoil Shape Opitimazition Using a Non uniform Rational B-splines Parameterization Under Thickness Constraint[J]. AIAA Journal. October 2006. 2170-2178
[23]焦予秦.风动侧壁干扰和结合部拐角粘性流动的N-S方程数值模拟[D] .西安:西北工业大学, 2000
[24]吴子牛.空气动力学[M] .北京:清华大学出版社, 2007: 286-289
[25]李为吉.飞机总体设计[M] .西安:西北工业大学出版社, 2004: 11-17
[26]索别茨基.高速运输机设计的新概念[M] .北京:国防工业出版社, 2001: 23-47
[27]张涵信.分离流与旋涡运动的结构分析[M] .北京:国防工业出版社, 2002: 87-92
[28]张兆顺.湍流[M] .北京:国防工业出版社, 2002: 56-77
[29]徐华舫.空气动力学基础[M] .北京:北京航空学院出版社,1987
[30] Bloy A.W, Roberts D.G Aerodynamic characteristics of an aerofoil with small trailing edge flap. Wind Engineering [J], 1993, 19(3)
[31] Kentfiled J .A.C, Claelle E.J .The flow physics of the Gurney flaps devices for improving turbine blade performance Wind Engineering [J], 1993, 19(1)
[32] Samuel Greenhalgh. Lift enhancement due unsteady aerodynamics [J], AIAA-93-3538-CP, 1993
[33] Edward W.Kruppa. A wind tunnel investigation of the Kasper vortex concept t[J], AIAA-77-3100, 1977
[34]吴望一.流体力学[M] .北京:北京大学出版社,1982
[35]陈国良,王熙法,庄镇泉.遗传算法及其应用[M] .北京:人民邮电出版社, 1996
[36]伍贻兆.跨声速空气动力学[M].北京:国防工业出版社,2004
[37]邢宗文.流体力学基础[M].西安:西北工业大学出版社,1992
[38]朱国林,王开春,金刚.飞机增生装置气动特性计算方法研究[J].空气动力学报, 2001, 19(2) : 148-155
[39]朱自强,马侠,陈炳永.跨声速粘流的计算[J].航空学报, 1991, 12(10) : 483-493
[40]崔桂香,许春晓,张兆顺.湍流大涡模拟进展[J].空气动力学报, 2004, 22(2) : 121-129
[41]夏商周,申振华.改型尾缘对翼型流场影响的数值模拟[J].沈阳航空工业学院学报, 2005, 22(5)
[42] Fiebeck R.H. Design of subsonic airfoils for high lift [J], J of Aircra1978,15(9)
[43] P.W.Bearman. Investigation of the flow behind a two-dimensional model with a blunt trailing edge and fitted with splitter plates, Fluid Mech [J], 21(2), 1965
[44]陈乃兴,张宏武,徐燕骥.叶型中弧线的最大弯度位置对跨音速压气机叶片性能影响的研究[J].工程热物理学报,2005, 26(3) : 409-412
[45]刘周,朱自强,付鸿雁.高升阻比翼型的设计[J].空气动力学学报,2003, 22(4) : 109-116
[46]孙刚,乔志德.机翼2机身2吊架2短舱的跨声速流计算[J].空气动力学学报, 1995, 13(4) : 374- 381
[47]熊俊涛,乔志德,韩忠华.响应面方法在跨声速翼型气动[J].西北工业大学学报, 2006, 24(2) : 232-236
[48]陆志良.跨声速机翼非定常气动力的全位势粘位迭代计算[J].空气动力学学报, 1998, 16(4) : 462-467
[49]李军,丰镇平,常建忠.透平叶栅C型网格生成技术的研究[J].西安交通大学学报, 1997, 31(12) : 44-48
[50] Thomas R. Barrett, Neilw Bressloff, Andy J Keane. Airfoil Design and Optimization Using Mutifidelity Analysis and Embedded Inverse Design [J]. AIAA Journal. September 2006. 2051-2059
[51] Razvan Florea, Kennethc Hall. Sensitivity Analysis of Unsteady Invisid Flow Through Turbomachinery Cascade[J]. AIAA Journal. June 2001.1047-1055
[52] J.C.Lin, F.G.Howard and G.V.Selby, Small Submerged Vortex Generators for Turbulent Flow Separation Control [J]. Journal of Space craft ,V ol.27,N o.5,1 990, pp503-507
[53]程玉庆,焦予秦.喷气吹气襟翼对翼型气动性能影响的研究[J].航空计算技术, 2006, 36(1) : 100- 102
[54]刘宝杰,杨晓宁,沈遐龄.翼型气动性能改进的实验研究[J].空气动力学学报, 1999, 20(1) : 53-56
[55] Storms B.L, Jang C.S. Lift enhancement of an airfoil using a Gurney Flap and Vortex Generation Journal of Aircraft [J].1994, 31(3)
[2]陈在薪,刘福长,鲍国华.空气动力学[D] .北京:航空工业出版社, 1993
[3]陶洋.实体鼓包改进超临界翼型气动特性数值计算及风洞试验研究[D] .绵阳:中国空气动力发展研究中心, 2004
[4]李亚臣,王晋军.发散后缘与Gurney襟翼对超临界翼型影响的实验研究[A].全国实验流体力学学术会议, 2005: 295-299
[5]李亚臣,王晋军,樊建超.超临界翼型Gurney襟翼增生研究[J].北京航空航天大学学报, 2003, 29(6) : 471-474
[6]阎文成.超临界翼型附面层分离及控制方案研究[D] .西安:西北工业大学, 2004
[7]阎超,谢磊,李云晓.翼型的气动最优化设计方法和反设计方法[J].空气动力学报, 1999, 17(1) : 61-67
[8]钱瑞战,乔志德,宋文萍.基于N-S方程的跨声速翼型多目标、多约束优化设计[J].空气动力学报, 2000, 18(3) : 350-353
[9]罗惕乾.流体力学[M] .北京:机械工业出版社, 2003: 267-276
[10]钱翼稷.空气动力学[M] .北京:北京航空航天大学出版社, 2004: 284-304
[11]方宝瑞.飞机气动布局设计[M] .北京:航空工业出版社, 1997: 525-547
[12]赖巍.高功率风力机叶型数值模拟及实验研究[D] .沈阳:沈阳航空工业学院, 2007
[13]夏商周.高高升力翼型数值模拟[D] .沈阳:沈阳航空工业学院, 2006
[14]章子雄,董曾男.粘性流体力学[M] .北京:清华大学出版社, 1998: 135-137
[15]李杰. Navier-Stokes方程数值模拟及湍流模型研究[D] .西安:西北工业大学, 2006
[16]王福军.计算流体动力学分析[M].北京:清华大学出版社, 2005 :120-126
[17]阎超.计算流体力学方法及应用[M] .北京:北京航空航天大学出版社, 2006: 227-228
[18]柳森.动翼型跨声速非定常粘性绕流的数值模拟[D] .西安:西北工业大学, 1993
[19]李孝伟,孙刚,乔志德.欧拉方程多段翼型绕流计算的嵌套网格方法[J].空气动力学学报, 1998, 16(4) : 492-497
[20]杨青.超临界翼型、机翼的定常和非定常流场数值模拟[D] .西安:西北工业大学, 2004
[21] Q.Xiao, H.M.Tsai, F.Liu. Numerical Study of Transonic Buffet On a Supercritical Airfoil [J]. AIAA Journal. March 2006.620-627
[22] Simon Parinchand-Ouellet, Christophe Tribes, Jean-Ynes Trepanier. Airfoil Shape Opitimazition Using a Non uniform Rational B-splines Parameterization Under Thickness Constraint[J]. AIAA Journal. October 2006. 2170-2178
[23]焦予秦.风动侧壁干扰和结合部拐角粘性流动的N-S方程数值模拟[D] .西安:西北工业大学, 2000
[24]吴子牛.空气动力学[M] .北京:清华大学出版社, 2007: 286-289
[25]李为吉.飞机总体设计[M] .西安:西北工业大学出版社, 2004: 11-17
[26]索别茨基.高速运输机设计的新概念[M] .北京:国防工业出版社, 2001: 23-47
[27]张涵信.分离流与旋涡运动的结构分析[M] .北京:国防工业出版社, 2002: 87-92
[28]张兆顺.湍流[M] .北京:国防工业出版社, 2002: 56-77
[29]徐华舫.空气动力学基础[M] .北京:北京航空学院出版社,1987
[30] Bloy A.W, Roberts D.G Aerodynamic characteristics of an aerofoil with small trailing edge flap. Wind Engineering [J], 1993, 19(3)
[31] Kentfiled J .A.C, Claelle E.J .The flow physics of the Gurney flaps devices for improving turbine blade performance Wind Engineering [J], 1993, 19(1)
[32] Samuel Greenhalgh. Lift enhancement due unsteady aerodynamics [J], AIAA-93-3538-CP, 1993
[33] Edward W.Kruppa. A wind tunnel investigation of the Kasper vortex concept t[J], AIAA-77-3100, 1977
[34]吴望一.流体力学[M] .北京:北京大学出版社,1982
[35]陈国良,王熙法,庄镇泉.遗传算法及其应用[M] .北京:人民邮电出版社, 1996
[36]伍贻兆.跨声速空气动力学[M].北京:国防工业出版社,2004
[37]邢宗文.流体力学基础[M].西安:西北工业大学出版社,1992
[38]朱国林,王开春,金刚.飞机增生装置气动特性计算方法研究[J].空气动力学报, 2001, 19(2) : 148-155
[39]朱自强,马侠,陈炳永.跨声速粘流的计算[J].航空学报, 1991, 12(10) : 483-493
[40]崔桂香,许春晓,张兆顺.湍流大涡模拟进展[J].空气动力学报, 2004, 22(2) : 121-129
[41]夏商周,申振华.改型尾缘对翼型流场影响的数值模拟[J].沈阳航空工业学院学报, 2005, 22(5)
[42] Fiebeck R.H. Design of subsonic airfoils for high lift [J], J of Aircra1978,15(9)
[43] P.W.Bearman. Investigation of the flow behind a two-dimensional model with a blunt trailing edge and fitted with splitter plates, Fluid Mech [J], 21(2), 1965
[44]陈乃兴,张宏武,徐燕骥.叶型中弧线的最大弯度位置对跨音速压气机叶片性能影响的研究[J].工程热物理学报,2005, 26(3) : 409-412
[45]刘周,朱自强,付鸿雁.高升阻比翼型的设计[J].空气动力学学报,2003, 22(4) : 109-116
[46]孙刚,乔志德.机翼2机身2吊架2短舱的跨声速流计算[J].空气动力学学报, 1995, 13(4) : 374- 381
[47]熊俊涛,乔志德,韩忠华.响应面方法在跨声速翼型气动[J].西北工业大学学报, 2006, 24(2) : 232-236
[48]陆志良.跨声速机翼非定常气动力的全位势粘位迭代计算[J].空气动力学学报, 1998, 16(4) : 462-467
[49]李军,丰镇平,常建忠.透平叶栅C型网格生成技术的研究[J].西安交通大学学报, 1997, 31(12) : 44-48
[50] Thomas R. Barrett, Neilw Bressloff, Andy J Keane. Airfoil Design and Optimization Using Mutifidelity Analysis and Embedded Inverse Design [J]. AIAA Journal. September 2006. 2051-2059
[51] Razvan Florea, Kennethc Hall. Sensitivity Analysis of Unsteady Invisid Flow Through Turbomachinery Cascade[J]. AIAA Journal. June 2001.1047-1055
[52] J.C.Lin, F.G.Howard and G.V.Selby, Small Submerged Vortex Generators for Turbulent Flow Separation Control [J]. Journal of Space craft ,V ol.27,N o.5,1 990, pp503-507
[53]程玉庆,焦予秦.喷气吹气襟翼对翼型气动性能影响的研究[J].航空计算技术, 2006, 36(1) : 100- 102
[54]刘宝杰,杨晓宁,沈遐龄.翼型气动性能改进的实验研究[J].空气动力学学报, 1999, 20(1) : 53-56
[55] Storms B.L, Jang C.S. Lift enhancement of an airfoil using a Gurney Flap and Vortex Generation Journal of Aircraft [J].1994, 31(3)