可降低气动热效应的类凹腔外形优化设计
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摘要
针对飞行器上由凸起物形成的类凹腔气动加热问题,采用数值方法求解三维N-S方程,研究了类凹腔外形结构的高超声速气动加热规律,获得了三维高超声速流场和局部热流分布,并详细分析了局部的流场结构和气动加热机理。针对凹腔前壁面热流密度过高的问题,提出并验证了一种降低前壁面边缘热流密度的优化外形,将前壁面的热流密度降低至优化前的20%左右。
The three-dimension Navier-Stokes equations are solved to reveal the aerothermal behavior of the cavity-like structure of protuberance on the surface of flight vehicles. Based on the calculated supersonic flow field and the local heat flux, the aerothermodynamic mechanism of the cavity-like structure is discussed. It is indicated that the heat flux peak is at the front edge of the cavity. An optimized shape is designed for reducing the peak value of the heat flux injected to the front edge. It is shown that the heat-flux onto the front wall is reduced to only about 20 percent of the initial value with the original shape.
The three-dimension Navier-Stokes equations are solved to reveal the aerothermal behavior of the cavity-like structure of protuberance on the surface of flight vehicles. Based on the calculated supersonic flow field and the local heat flux, the aerothermodynamic mechanism of the cavity-like structure is discussed. It is indicated that the heat flux peak is at the front edge of the cavity. An optimized shape is designed for reducing the peak value of the heat flux injected to the front edge. It is shown that the heat-flux onto the front wall is reduced to only about 20 percent of the initial value with the original shape.
引文
[1]李素循.激波与边界层主导的复杂流动[M].北京:科学出版社,2007:4-11
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[10]贾真,吴迪,朴英,等.凹腔前缘角对超声速燃烧室性能的影响[J].航空动力学报,2012,27(5):993-998JIA Z,WU D,PIAO Y,et al.Effect of cabity leading edge angle on performance of supersonic combustor[J].Journal of Aerospace Power,2012,27(5):993-998
[11]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,2007:27-28
[12]阎超,禹建军,李君哲.热流CFD计算中格式和网格效应若干问题研究[J].空气动力学学报,2006,24(1):125-130YAN C,YU J J,LI J Z.Scheme effect and grid dependency in CFD computations of heat trans[J].Acta Aerodynamica Sinica,2006,24(1):125-130
[2]唐功跃,吴国庭,姜贵庆.缝隙流动分析及其热环境的工程计算[J].中国空间科学技术,1996,16(6):1-7
[3]CHAPMAN D R A.Theoretical analysis of heat transfer in regions of separated flow:NACA-TN 3792[R],1956
[4]BURGGRAF O R.A model of steady separated flow in rectangular caviies at high Reynolds number[C]//Proceedings of the 1965 Heat Transfer and Fluid Mechanics Institute.Palo Alto:Stanford University Press,1965:190-229
[5]BENYAKAR A,HANSON R K.Supersonic combustion of cross flow jets and the influence of cavity flame holders:AIAA-99-0484[R],1999
[6]NESTLER D E,SAYDAH A R,AUXER W L.Heat transfer to steps and cavities in hypersonic turbulent flow[C]//AIAA Fluid and Plasma Dynamics Conference.Los Angeles,California,1968
[7]童秉纲.航天飞机防热瓦缝隙气动加热的讨论[J].气动试验与测量控制,1999,4(4):1-8TONG B G.A qualitative study of the gap heating on space shuttle[J].Aerodynamic Experiment and Measurement&Control,1999,4(4):1-8
[8]龚红明,陈景秋,李理.湍流条件下防热瓦缝隙热环境特性实验研究[J].实验流体力学,2015,29(2):13-18GONG H M,CHEN J Q,LI L.Experimental investigation on the aerodynamic heating to tile-to-tile gaps in turbulent boundary layer[J].Journal of Experiments in Fluid Mechananics,2015,29(2):13-18
[9]房田文,丁猛,周进.凹腔超声速流场结构的试验研究[J].国防科技大学学报,2007,29(3):1-5FANG T W,DING M,ZHOU J.Experimental investigation on supersonic flows over cavities[J].Journal of National University of Defense Technology,2007,29(3):1-5
[10]贾真,吴迪,朴英,等.凹腔前缘角对超声速燃烧室性能的影响[J].航空动力学报,2012,27(5):993-998JIA Z,WU D,PIAO Y,et al.Effect of cabity leading edge angle on performance of supersonic combustor[J].Journal of Aerospace Power,2012,27(5):993-998
[11]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,2007:27-28
[12]阎超,禹建军,李君哲.热流CFD计算中格式和网格效应若干问题研究[J].空气动力学学报,2006,24(1):125-130YAN C,YU J J,LI J Z.Scheme effect and grid dependency in CFD computations of heat trans[J].Acta Aerodynamica Sinica,2006,24(1):125-130
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