Large Eddy Simulation of Crossflow Transition Characteristics in Hypersonic Elliptic Cone Boundary Layer
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摘要: 横流效应显著影响高超声速飞行器的三维边界层转捩过程, 深化对该流动机制的认识有助于提升和改善飞行器气动性能及热力学环境. 针对HIFiRE5椭圆锥绕流问题, 采用大涡模拟方法计算分析了超声速边界层横流转捩特性, 并揭示其中的流动机理. 参考HIFiRE5风洞模型试验条件, 数值模拟中椭圆锥来流入口处施加人工速度扰动以激发边界层内不稳定扰动波, 进而预测了高超声速边界层流动横流失稳、转捩过程等基本流动特征, 并基于转捩热流分布形态对比, 获得了与试验数据基本吻合的计算结果. 研究发现, 椭圆锥中心线流动汇聚形成的流向涡结构非常容易失稳, 另外在中心线及侧缘之间的中部区域存在较强的横流不稳定性, 两种机制共同作用影响边界层转捩过程. 此外, 分析了来流扰动幅值对边界层横流失稳转捩的影响, 并发现静来流条件下, 横流区域出现两组独立的定常横流涡结构, 而强噪声来流条件下, 中心线主涡和中部横流涡均发生失稳转捩, 且在椭圆锥表面形成多峰状的转捩阵面. 最后, 深入分析流场的压力脉动动力学特性, 揭示了三维边界层发生失稳转捩的非线性演化机制.Abstract: The crossflow effect significantly affects the three-dimensional boundary layer transition process of hypersonic vehicle. Deepening the understanding of the flow mechanism is helpful to improve the aerodynamic performance and thermodynamic environment of hypersonic vehicle. Aiming at the flow around HIFiRE5 elliptic cone, the characteristics of cross-flow transition in supersonic boundary layer were calculated and analyzed by using large eddy simulation method, and the flow mechanism was revealed. Referring to the HIFiRE5 model test conditions of wind tunnel, in the numerical simulation, an artificial velocity disturbance was applied at the inlet of the elliptic cone to excite the unstable disturbance wave in the boundary layer, and then the basic flow characteristics such as crossflow instability and transition in the hypersonic boundary layer were predicted. Based on the comparison of transition heat flow distribution, it was proved that the calculation results were basically consistent with the experimental data. It is found that the streamwise vortex structure formed by the flow convergence on the center line of the elliptic cone is very easy to become unstable. In addition, there is a strong crossflow instability in the middle region between the center line and the side edge. The two mechanisms affect the boundary layer transition together. Furthermore, the influence of the amplitude of the inflow disturbance on the crossflow instability transition in the boundary layer was analyzed. It is found that under the quiet inflow condition, two groups of independent steady crossflow vortex structures appear in the crossflow region, while under the noisy inflow condition, the instability transition occurs in the main vortex of the centerline and the middle crossflow vortex, and a multi-peak transition front is formed on the surface of the elliptic cone. Finally, the dynamic characteristics of pressure fluctuation in the flow field were deeply analyzed, and the nonlinear evolution mechanism of instability transition in three-dimensional boundary layer was revealed.
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Key words:
- crossflow /
- transition /
- boundary layer /
- hypersonic /
- large eddy simulation
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图 3 数值结果与风洞试验热流数据对比
Figure 3. Heat-flux comparison between numerical results and wind tunnel experimental data
图 8 不同扰动幅值下瞬态涡系结构(Q2=0.01)
Figure 8. Instantaneous vortex structures under different disturbance amplitudes (Q2=0.01)
图 9 不同扰动幅值下瞬态、时均热流分布
Figure 9. Instantaneous and time-averaged heat flux distributions under different disturbance amplitudes
图 12 不同扰动幅值密度脉动均方根、湍动能对比
Figure 12. Comparison of root mean square of density fluctuation and turbulent kinetic energy between different disturbance amplitudes
表 1 风洞试验工况
Table 1. Condition of wind tunnel experiment
Ma Re/m-1 T/K P/kPa 5.8 10.2×106 410 810 
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[1] 向星皓, 张毅锋, 陈坚强, 等. 横流转捩模型研究进展[J]. 空气动力学学报, 2018, 36(2): 254-264. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201802010.htmXiang X H, Zhang Y F, Chen J Q, et al. Progress in transition models for cross-flow instabilities[J]. Acta Aerodynamica Sinica, 2018, 36(2): 254-264(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201802010.htm [2] 沈清, 袁湘江, 王强, 等. 可压缩边界层与混合层失稳结构的研究进展及其工程应用[J]. 力学进展, 2012, 42(3): 252-261. https://www.cnki.com.cn/Article/CJFDTOTAL-LXJZ201203004.htmShen Q, Yuan X J, Wang Q, et al. Review on the instability structure in compressible boundary layers and mixing layers and its application[J]. Advances in Mechanics, 2012, 42(3): 252-261(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-LXJZ201203004.htm [3] 杨武兵, 沈清, 朱德华, 等. 高超声速边界层转捩研究现状与趋势[J]. 空气动力学学报, 2018, 36(2): 183-195. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201802004.htmYang W B, Shen Q, Zhu D H, et al. Tendency and current status of hypersonic boundary layer transition[J]. Acta Aerodynamica Sinica, 2018, 36(2): 183-195(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201802004.htm [4] Holden M S, Wadhams T P, MacLean M, et al. Reviews of studies of boundary layer transition in hypersonic flows over axisymmetric and elliptic cones conducted in the CUBRC shock tunnels[R]. AIAA 2009-0782, 2009. [5] Berger K T, Rufer S J, Kimmel R, et al. Aerothermodynamic characteristics of boundary layer transition and trip effectiveness of the HIFiRE Flight 5 vehicle[R]. AIAA 2009-4055, 2009. [6] Juliano T J, Schneider S P. Instability and transition on the HIFiRE-5 in a Mach 6 quiet tunnel[R]. AIAA 2010-5004, 2010. [7] Juliano T J, Borg M P, Schneider S P. Quiet tunnel measurements of HIFiRE-5 boundary-layer transition[J]. AIAA Journal, 2015, 53(4): 832-846. doi: 10.2514/1.J053189 [8] Borg M P, Kimmel R, Stanfield S. HIFiRE-5 attachment-line and cross flow instability in a quiet hypersonic wind tunnel[R]. AIAA 2011-3247, 2011. [9] Borg M P, Kimmel R L, Stanfield S. Crossflow instability for HIFiRE-5 in a quiet hypersonic wind tunnel[R]. AIAA 2012-2821, 2012. [10] Borg M P, Kimmel R L, Stanfield S. Traveling crossflow instability for HIFiRE-5 in a quiet hypersonic wind tunnel[R]. AIAA 2013-2737, 2013. [11] Juliano T J, Poggie J, Porter K M, et al. HIFiRE-5b heat flux and boundary-layer transition[R]. AIAA 2017-3134, 2017. [12] Choudhari M, Chang C L, Jentink T, et al. Transition analysis for the HIFiRE-5 vehicle[R]. AIAA 2009-4056, 2009. [13] Gosse R, Kimmel R, Johnson H B. CFD study of the HiFiRE-5 flight experiment[R]. AIAA 2010-4854, 2010. [14] Li F, Choudhari M, Chang CL, et al. Stability analysis for HIFiRE experiments[R]. AIAA 2012-2961, 2012. [15] Dinzl D J, Candler G V. Direct numerical simulation of crossflow instability excited by microscale roughness on HIFiRE-5[R]. AIAA 2016-0353, 2016. [16] Tufts M W, Borg M P, Bisek N J, et al. High-fidelity simulation of HIFiRE-5 boundary-layer transition[R]. AIAA 2020-3025, 2020. [17] Boris J P, Grinstein F F, Oran E S, et al. New insights into large eddy simulation[J]. Fluid Dynamics Research, 1992, 10(4/6): 199-228. [18] Garnier E, Adams N, Sagaut P. Large eddy simulation for compressible flows[M]. Dordrecht: Springer, 2009. [19] Lu X Y, Wang S W, Sung H G, et al. Large-eddy simulations of turbulent swirling flows injected into a dump chamber[J]. Journal of Fluid Mechanics, 2005, 527(1): 171-196. [20] 朱志斌, 袁湘江, 陈林. 适用于超声速流场计算的有限体积紧致算法[J]. 航空动力学报, 2015, 30(10): 2481-2487. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201510023.htmZhu Z B, Yuan X J, Chen L. Finite volume compact algorithm suited to computation of supersonic flow field[J]. Journal of Aerospace Power, 2015, 30(10): 2481-2487(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201510023.htm [21] 朱志斌, 潘宏禄, 程晓丽. 钝头双锥喷流致冷流场结构及密度脉动特性[J]. 航空动力学报, 2019, 34(7): 1425-1432. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201907003.htmZhu Z B, Pan H L, Cheng X L. Flow field structures and density fluctuation characteristics around a blunted double cone with cooling jet[J]. Journal of Aerospace Power, 2019, 34(7): 1425-1432(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201907003.htm [22] 张红军, 朱志斌, 尚庆, 等. 锯齿形转捩片触发高超声速进气道边界层转捩的大涡模拟[J]. 航空学报, 2019, 40(10): 122930. https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201910011.htmZhang H J, Zhu Z B, Shang Q, et al. Large eddy simulation of hypersonic inlet boundary layer transition triggered by zig-zag trip[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(10): 122930(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKXB201910011.htm [23] 朱志斌, 程晓丽, 潘宏禄. 超声速喷流混合流场大涡模拟[J]. 航空动力学报, 2019, 34(1): 210-216. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201901023.htmZhu Z B, Cheng X L, Pan H L. Large eddy simulation of supersonic jet mixing flow[J]. Journal of Aerospace Power, 2019, 34(1): 210-216(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201901023.htm [24] Poggie J, Bisek N J, Gosse R. Resolution effects in compressible, turbulent boundary layer simulations[J]. Computers & Fluids, 2015, 120: 57-69. [25] 吕金虎, 陆君安, 陈士华. 混沌时间序列分析及其应用[M]. 武汉: 武汉大学出版社, 2002.Lv J H, Lu J A, Chen S H. Chaotic time series analysis and its application[M]. Wuhan: Wuhan University Press, 2002(in Chinese). [26] Wolf A, Swift J B, Swinney H L, et al. Determining Lyapunov exponents from a time series[J]. Physica D: Nonlinear Phenomena, 1985, 16(3): 285-317. doi: 10.1016/0167-2789(85)90011-9 -
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