振动激发对高超声速气动力/热影响
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摘要
随着飞行马赫数的不断提高,空气的高温气体效应越来越明显,对高超声速飞行器的气动力/热特性产生重要影响.高温气体效应对气动力/热的影响机理复杂,影响参数众多,迄今为止国内外尚未完全研究清楚.发生高温气体效应时,多个非线性物理过程耦合在一起,地面试验和数值模拟无法将这些过程解耦,无法给出关键物理机理.为了解决这一问题,文章提出一种理论分析与数值模拟相结合的两步渐进新方法:先通过牛顿迭代法得到发生振动激发过程的斜激波无黏解;再将该无黏解的结果作为边界条件,求解边界层的黏性解.利用该方法研究了振动激发过程对二维斜劈的气动力/热特性的影响规律.研究结果表明,振动激发过程对斜激波后的温度、密度、马赫数、雷诺数和斜激波角影响较大,而对压力和速度影响较小.斜激波波后的无黏流动与边界层流动是耦合在一起的.发生振动激发后,斜激波波后雷诺数的增大会导致边界层厚度减小,结合多个物理量的变化,如速度增大和温度减小,共同对边界层内的摩擦阻力和气动热产生影响.对比完全气体的结果发现,振动激发使壁面摩阻升高,而使壁面热流降低.分别通过影响激波层和边界层,振动激发对摩阻的影响是弱耦合的,而对热流的影响则是强耦合的.
With the increasing of flight Mach number, the high-temperature gas effect of air has becoming remarkable,which has significant impacts on the aerodynamics and aerothermodynamic characteristics of hypersonic vehicles. Because of the complex mechanism and numerous key parameters of high-temperature gas effect, it has not been fully studied at home and abroad. When the high-temperature gas effect occurs, multiple nonlinear physical processes are coupled together. However, ground tests and numerical simulations can not decouple these processes and can not explain the key physical mechanisms. To solve this problem, a new two-step asymptotic approximation method combining theoretic analysis and numerical simulation is proposed. In this method, the oblique shock relation with vibration excitation effect is obtained by Newton iterative method, then the results are used as the boundary conditions of the boundary layer andit is solved numerically. By using this method, the effect of vibration excitation on the aerodynamics and aerothermodynamic characteristics of a two dimensional wedge is studied. The results show that, the vibration excitation process has great effect on the shock angle, the temperature, density, Mach number, and Reynolds number behind the oblique shock,but little influence on the pressure and velocity. The inviscid flow behind the oblique shock is coupled together with the boundary layer flow. The changes of multiple physical quantities, including the increase of velocity and the decrease of the temperature behind the oblique shock, and the decrease of the boundary layer thickness due to the increase of the Reynolds number, have an effect on the friction and aerodynamic heating in the boundary layer. Comparing with perfect gas model, vibration excitation increases the wall friction and decreases the wall heat flux of the wedge. By influencing the shock layer and the boundary layer respectively, the effects of vibration excitation on heat flux are strong coupled,while they are weak coupled on friction.
With the increasing of flight Mach number, the high-temperature gas effect of air has becoming remarkable,which has significant impacts on the aerodynamics and aerothermodynamic characteristics of hypersonic vehicles. Because of the complex mechanism and numerous key parameters of high-temperature gas effect, it has not been fully studied at home and abroad. When the high-temperature gas effect occurs, multiple nonlinear physical processes are coupled together. However, ground tests and numerical simulations can not decouple these processes and can not explain the key physical mechanisms. To solve this problem, a new two-step asymptotic approximation method combining theoretic analysis and numerical simulation is proposed. In this method, the oblique shock relation with vibration excitation effect is obtained by Newton iterative method, then the results are used as the boundary conditions of the boundary layer andit is solved numerically. By using this method, the effect of vibration excitation on the aerodynamics and aerothermodynamic characteristics of a two dimensional wedge is studied. The results show that, the vibration excitation process has great effect on the shock angle, the temperature, density, Mach number, and Reynolds number behind the oblique shock,but little influence on the pressure and velocity. The inviscid flow behind the oblique shock is coupled together with the boundary layer flow. The changes of multiple physical quantities, including the increase of velocity and the decrease of the temperature behind the oblique shock, and the decrease of the boundary layer thickness due to the increase of the Reynolds number, have an effect on the friction and aerodynamic heating in the boundary layer. Comparing with perfect gas model, vibration excitation increases the wall friction and decreases the wall heat flux of the wedge. By influencing the shock layer and the boundary layer respectively, the effects of vibration excitation on heat flux are strong coupled,while they are weak coupled on friction.
引文
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3 Anderson JD.Hypersonic and High-Temperature Gas Dynamics,2nd Edition.AIAA,2006
4童秉纲,孔祥言,邓国华.气体动力学.第2版.北京:高等教育出版社,2012(Tong Binggang,Kong Xiangyan,Deng Guohua.Gas Dynamics.2nd Edition.Beijing:Higher Education Press,2012(in Chinese))
5 Hirschel EH,Weiland C.Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles.Berlin:Springer,2009
6 Compton HR,Schiess JR,Suit WT,et al.Stability and control over the supersonic and hypersonic speed range.Conference Paper,NASA Langley,1983
7 Brauckmann GJ,Paulson JW.Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly.Journal of Spacecraft and Rockets,1995,32(5):758-764
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9 Griffith BJ,Maus JR,Best JT.Explanation of the hypersonic longitudinal stability problem:lessons learned.NASA,1983
10 Romere PO,Young JC.Space shuttle entry longitudinal aerodynamic comparisons of flight 2 with preflight predictions.Journal of Spacecraft and Rockets,1983,20(6):518-523
11 Calloway RL.Real-gas simulation for the shuttle orbiter and planetary entry configurations including flight results.AIAA,1984
12 Jiang ZL,Yu HR.Experimental and development of the longtest-duration hypervelocity detonation-driven shock tunnel(LHDst).AIAA,2014
13姜宗林,李进平,赵伟等.长试验时间爆轰驱动激波风洞技术研究.力学学报,2012,44(5):824-831(Jiang Zonglin,Li Jinping,Zhao Wei,et al.Investigating into techniques for extending the test-duration of detonation-driven shock tunnels.Chinese Journal of Theoretical and Applied Mechanics,2012,44(5):824-831(in Chinese))
14刘云峰,汪运鹏,苑朝凯等.复现高超声速飞行条件下10?尖锥标模气动力特性试验研究.中国力学大会,上海,2015(Liu Yunfeng,Wang Yunpeng,Yuan Chaokai,et al.Aerodynamic force and moment characteristics of 10 degree sharp cone at Mach 7.0 in JF12shock tunnel.The Chinese Congress of Theoretical and Applied Mechanics,Shanghai,2015(in Chinese))
15汪运鹏,刘云峰,苑朝凯等.长试验时间激波风洞测力技术研究.力学学报,2016,48(3):545-556(Wang Yunpeng,Liu Yunfeng,Yuan Chaokai,et al.Study on force measurement in long-test duration shock tunnel.Chinese Journal of Theoretical and Applied Mechanics,2016,48(3):545-556(in Chinese))
16汪志诚.热力学·统计物理.第4版.北京:高等教育出版社,2008(Wang Zhicheng.Thermodynamics&Statistical Physics.4th Edition.Beijing:Higher Education Press,2008(in Chinese))
17张德良.计算流体力学教程.北京:高等教育出版社,2010(Zhang Deliang.A Course in Computational Fluid Dynamics.Beijing:Higher Education Press,2010(in Chinese))
18任玉新,陈海昕.计算流体力学基础.北京:清华大学出版社,2006(Ren Yuxin,Chen Haixin.Fundamentals of Computational Fluid Dynamics.Beijing:Tsinghua University Press,2006(in Chinese))
19卞荫贵,徐立功.气动热力学.第2版.合肥:中国科学技术大学出版社,2010(Bian Yingui,Xu Ligong.Aerothermodynamics.2nd Edition.Hefei:University of Science and Technology of China Press,2010(in Chinese))
20 Seokkwan Y,Antony J.Lower-upper symmetric-gauss-seidel method for the Euler and Navier-Stokes equations.AIAA Journal,1988,26(9):1025-1026
21 Kim KH,Kim C,Rho OH.Methods for the accurate computations of hypersonic flows I.AUSMPW+scheme.Journal of Computational Physics,2001,174(1):38-80
22 Kim KH,Lee JH,Rho OH.An improvement of AUSM schemes by introducing the pressure-based weight functions.Computers&Fluids,1988,27(3):311-346
23 Keiichi K,Eiji S,Yoshiaki N,et al.Evaluation of Euler flux for hypersonic heating computations.AIAA Journal,2010,48(4):763-776
24 Ren Yuxin.A robust shock-capturing scheme based on rotated Riemann solvers.Computers&Fluid,2003,32(10):1379-1403
25 Van Leer B.Towards to the ultimate conservation difference schemes:V.a second-order sequel to Godunov method.Journal of Computational Physics,1979,32(1):101-136
26 Collela P.A direct Eulerian MUSCL scheme for gas dynamics.SIAM Journal on Scientific and Statistical Computing,1985,6(1):104-117
2樊菁.高超声速高温气体效应判据.力学学报,2010,42(4):591-596(Fan Jing.Criteria on high-temperature gas effects around hypersonic vehicles.Chinese Journal of Theoretical and Applied Mechanics,2010,42(4):591-596(in Chinese))
3 Anderson JD.Hypersonic and High-Temperature Gas Dynamics,2nd Edition.AIAA,2006
4童秉纲,孔祥言,邓国华.气体动力学.第2版.北京:高等教育出版社,2012(Tong Binggang,Kong Xiangyan,Deng Guohua.Gas Dynamics.2nd Edition.Beijing:Higher Education Press,2012(in Chinese))
5 Hirschel EH,Weiland C.Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles.Berlin:Springer,2009
6 Compton HR,Schiess JR,Suit WT,et al.Stability and control over the supersonic and hypersonic speed range.Conference Paper,NASA Langley,1983
7 Brauckmann GJ,Paulson JW.Experimental and computational analysis of shuttle orbiter hypersonic trim anomaly.Journal of Spacecraft and Rockets,1995,32(5):758-764
8 Muylaert J,Walpot L,Rostand P,et al.Extrapolation from wind tunnel to flight:shuttle orbiter aerodynamics.Technical Report,NASALangley,1998
9 Griffith BJ,Maus JR,Best JT.Explanation of the hypersonic longitudinal stability problem:lessons learned.NASA,1983
10 Romere PO,Young JC.Space shuttle entry longitudinal aerodynamic comparisons of flight 2 with preflight predictions.Journal of Spacecraft and Rockets,1983,20(6):518-523
11 Calloway RL.Real-gas simulation for the shuttle orbiter and planetary entry configurations including flight results.AIAA,1984
12 Jiang ZL,Yu HR.Experimental and development of the longtest-duration hypervelocity detonation-driven shock tunnel(LHDst).AIAA,2014
13姜宗林,李进平,赵伟等.长试验时间爆轰驱动激波风洞技术研究.力学学报,2012,44(5):824-831(Jiang Zonglin,Li Jinping,Zhao Wei,et al.Investigating into techniques for extending the test-duration of detonation-driven shock tunnels.Chinese Journal of Theoretical and Applied Mechanics,2012,44(5):824-831(in Chinese))
14刘云峰,汪运鹏,苑朝凯等.复现高超声速飞行条件下10?尖锥标模气动力特性试验研究.中国力学大会,上海,2015(Liu Yunfeng,Wang Yunpeng,Yuan Chaokai,et al.Aerodynamic force and moment characteristics of 10 degree sharp cone at Mach 7.0 in JF12shock tunnel.The Chinese Congress of Theoretical and Applied Mechanics,Shanghai,2015(in Chinese))
15汪运鹏,刘云峰,苑朝凯等.长试验时间激波风洞测力技术研究.力学学报,2016,48(3):545-556(Wang Yunpeng,Liu Yunfeng,Yuan Chaokai,et al.Study on force measurement in long-test duration shock tunnel.Chinese Journal of Theoretical and Applied Mechanics,2016,48(3):545-556(in Chinese))
16汪志诚.热力学·统计物理.第4版.北京:高等教育出版社,2008(Wang Zhicheng.Thermodynamics&Statistical Physics.4th Edition.Beijing:Higher Education Press,2008(in Chinese))
17张德良.计算流体力学教程.北京:高等教育出版社,2010(Zhang Deliang.A Course in Computational Fluid Dynamics.Beijing:Higher Education Press,2010(in Chinese))
18任玉新,陈海昕.计算流体力学基础.北京:清华大学出版社,2006(Ren Yuxin,Chen Haixin.Fundamentals of Computational Fluid Dynamics.Beijing:Tsinghua University Press,2006(in Chinese))
19卞荫贵,徐立功.气动热力学.第2版.合肥:中国科学技术大学出版社,2010(Bian Yingui,Xu Ligong.Aerothermodynamics.2nd Edition.Hefei:University of Science and Technology of China Press,2010(in Chinese))
20 Seokkwan Y,Antony J.Lower-upper symmetric-gauss-seidel method for the Euler and Navier-Stokes equations.AIAA Journal,1988,26(9):1025-1026
21 Kim KH,Kim C,Rho OH.Methods for the accurate computations of hypersonic flows I.AUSMPW+scheme.Journal of Computational Physics,2001,174(1):38-80
22 Kim KH,Lee JH,Rho OH.An improvement of AUSM schemes by introducing the pressure-based weight functions.Computers&Fluids,1988,27(3):311-346
23 Keiichi K,Eiji S,Yoshiaki N,et al.Evaluation of Euler flux for hypersonic heating computations.AIAA Journal,2010,48(4):763-776
24 Ren Yuxin.A robust shock-capturing scheme based on rotated Riemann solvers.Computers&Fluid,2003,32(10):1379-1403
25 Van Leer B.Towards to the ultimate conservation difference schemes:V.a second-order sequel to Godunov method.Journal of Computational Physics,1979,32(1):101-136
26 Collela P.A direct Eulerian MUSCL scheme for gas dynamics.SIAM Journal on Scientific and Statistical Computing,1985,6(1):104-117