新型高超声速进气道边界层人工转捩方法研究
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摘要
为确保高超声速进气道的安全工作,其压缩面边界层在进入其内流道前必须完成转捩。针对高超声速进气道边界层转捩需要,依据二维高超声速边界层转捩机理,尝试了一种新型低阻高效的边界层人工转捩方法,在FD-07风洞中开展了试验验证。试验中首先通过进气道对称面压力分布和激波纹影获得进气道的自起动情况,进而推断进气道入口前的边界层转捩情况。试验包括进气道前体边界层自然转捩和人工转捩,试验结果表明在Ma=5、6,迎角α=0°来流条件下,使用同一波长的人工转捩带可以成功实现进气道边界层转捩,验证了基于线性稳定性理论设计的人工转捩带在宽马赫数范围的适用性。
In order to ensure the robustness of the scramjet propulsion system,the boundary layer approaching the hypersonic inlet should be turbulent.To develop boundary layer strips for the hypersonic vehicle,a new promising strip configuration with low drag and high efficiency was designed based on the theory of two dimensional hypersonic boundary layer transition and was tested in FD-07 wind tunnel.Whether the inlet is started or not can reflect the boundary layer/shock interaction.The pressure distribution of inlet symmetry planes and shock schlieren will be distinctively deferent for laminar and turbulent on the effect of incident shock,so pressure distribution of inlet symmetrical and shock schlieren were used to identify the inlet starting or not and the situation of boundary layer transition can be judged by inlet starting.The tests were conducted including natural transition and artificial transition.The test results show that the boundary layer can be transited successfully using the same strip under the condition of Ma=5and 6,α=0°,and thus verifies the applicability of the strip which is designed based on the Linear Steady Theory in a wide range of Mach numbers.
In order to ensure the robustness of the scramjet propulsion system,the boundary layer approaching the hypersonic inlet should be turbulent.To develop boundary layer strips for the hypersonic vehicle,a new promising strip configuration with low drag and high efficiency was designed based on the theory of two dimensional hypersonic boundary layer transition and was tested in FD-07 wind tunnel.Whether the inlet is started or not can reflect the boundary layer/shock interaction.The pressure distribution of inlet symmetry planes and shock schlieren will be distinctively deferent for laminar and turbulent on the effect of incident shock,so pressure distribution of inlet symmetrical and shock schlieren were used to identify the inlet starting or not and the situation of boundary layer transition can be judged by inlet starting.The tests were conducted including natural transition and artificial transition.The test results show that the boundary layer can be transited successfully using the same strip under the condition of Ma=5and 6,α=0°,and thus verifies the applicability of the strip which is designed based on the Linear Steady Theory in a wide range of Mach numbers.
引文
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[2]全鹏程,易仕和,武宇,等.激波与层流/湍流边界层相互作用实验研究[J].物理学报,2014,8(63):1-5.Quan P C,Yi S H,Wu Y,et al.Experimental investigation of interactions between laminar or turbulent boundary layer and shock wave[J].Acta Phys Sin,2014,8(63):1-5.
[3]Anderson E C,Lewis C H.Laminar or turbulent boundary layer flows of perfect gases or reacting gas mixtures in chemical equilibrium[R].NASA CR-1893,1971.
[4]Berry S A,Nowak R J,Horvath T J.Boundary layer control for hypersonic airbreathing vehicles[R].AIAA-2004-2246,2004.
[5]Berry S A,DiFulvio M,Kowalkowski M K.Forced boundarylayer transition on X-43(Hyper-X)in NASA LaRC 31-inch Mach 10air tunnel[R].NASA Langley Research Center,2000.
[6]Berry S A,DiFulvio M,Kowalkowski M K.Forced boundarylayer transition on X-43(Hyper-X)in NASA LaRC 20-inch Mach 6air tunnel[R].NASA Langley Research Center,2000.
[7]Berry S A,Daryabeigi K,Wurster K,et al.Boundary layer transition on X-43A[R].AIAA-2008-3736,2008.
[8]Matthew P B.Laminar instability and transition on the X-51[D].West Lafayette:Purdue University School of Aeronautics&Astronautics,2009.
[9]Kimmel R,Adamczak D,Gosse R.Ground test and computation of boundary layer transition on the hypersonic international flight research and experimentation HIFiRE-5 vehicle[R].AFRL-RB-WP-TR-2011-3025,2011.
[10]Hanifi A,Dahlkild A.Stability characteristics of 3-D boundary layer on a yawed cone[C]//Proceedings of the IUTAM Symposium,Sendai,1994.
[11]Fan Xiaoqiang,Yi Shihe,Jia Di,et al.Forced boundary-layer transition of axisymmetric inlet in Mach 8gun wind tunnel and its numerical verification[R].AIAA-2005-3551,2005.
[12]赵慧勇,周瑜,倪鸿礼,等.高超声速进气道边界层强制转捩试验[J].实验流体力学,2012,26(1):1-6.Zhao H Y,Zhou Y,Ni H L,et al.Test of forced boundary-layer transition on hypersonic inlet[J].Journal of Experiments in Fluid Mechanics,2012,26(1):1-6.
[13]赵俊波,沈清,张红军,等.基于T-S波谐频共振的超燃进气道边界层转捩[J].航空动力学报,2010,25(11):2420-2424.Zhao J B,Shen Q,Zhang H J,et al.Boundary transition research of scramjet inlet based on the Tollmien-Schlichting(T-S)wave syntony[J].Journal of Aerospace Power,2010,25(11):2420-2424.
[14]张红军,沈清.高超声速进气道前缘钝度效应试验研究[J].推进技术,2013,34(10):1316-1320.Zhang H J,Shen Q.Experimental studies of leading edge bluntness effects on hypersonic inlet[J].Journal of Propusion Technology,2013,34(10):1316-1320.
[15]董亚妮,周恒.二维超音速边界层中三波共振和二次失稳机制的数值模拟研究[J].应用数学和力学,2006,27(2):127-133.Dong Y N,Zhou H.Numerical study for the resonant triad interaction and secondary instability in a two-dimensional supersonic boundary layer[J].Applied Mathematics and Mechanic,2006,27(2):127-133.
[16]潘宏禄,李俊红,沈清.超燃进气道激波/湍流边界层干扰[J].推进技术,2013,34(9):1172-1178.Pan H L,Li J H,Shen Q.Studies of turbulence/shock interaction in a scramjet inlet[J].Journal of Propulsion Technology,2013,34(9):1172-1178.