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[1]李永洲,李光熙,张堃元,等.前缘水平投影可控的乘波体设计方法研究[J].火箭推进,2017,43(05):20-27.
　LI Yongzhou,LI Guangxi,ZHANG Kunyuan,et al.Design method of waverider with controlled horizontal projection of leading edge[J].Journal of Rocket Propulsion,2017,43(05):20-27.
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前缘水平投影可控的乘波体设计方法研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 43 期数: 2017年05期 页码: 20-27 栏目: 研究与设计 出版日期: 2017-10-15
Title:
Design method of waverider with controlled horizontal projection of leading edge
作者:
李永洲1; 李光熙1; 张堃元2; 孙迪3
1. 西安航天动力研究所,陕西 西安 710100; 2.南京航空航天大学 能源与动力学院,江苏 南京 210016; 3.西安航天动力技术研究所,陕西 西安 710025
Author(s):
LI Yongzhou1; LI Guangxi1; ZHANG Kunyuan2; SUN Di3
1.Xi'an Aerospace Propulsion Institute,Xi'an 710100,China; 2.College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China; 3.Xi'an Institute of Aerospace Propulsion Technology,Xi'an 710025,China
关键词:
乘波体;  投影形状;  流线追踪;  混合函数;  密切面
Keywords:
waverider;  projection shape;  streamline tracing;  blend function;  osculating plane
分类号:
V221-34
文献标志码:
A
摘要:
结合流线追踪技术和密切面混合函数提出了一种前缘水平投影可控的乘波体设计方法,并完成了前缘水平投影为超椭圆的乘波体(Waverider-F)和超椭圆前缘转超椭圆后缘的乘波体(Waverider-FT)设计。二者具有较高的容积效率,前缘对应的轴向投影近似为余弦曲线。通过数值仿真验证了设计方法的有效性,设计点时Waverider-F的乘波特性良好且保持了基准流场的特点,Waverider-FT前部完全乘波,后部两侧诱导激波使流场变形且形成高压区,接力点时二者的乘波特性也较好。另外,二者具有较高的升阻比和预压缩效率,设计点时无粘升阻比分别为3.46和2.88。与Waverider-F相比,Waverider-FT的升力、阻力和出口增压比都明显增加,而升阻比、俯仰力矩和出口总压恢复系数降低。有粘条件下,设计点的升阻比由2.91降为2.41,对应的出口总压恢复系数降低了5.8%。
Abstract:
A design method of waverider with controlled horizontal projection of leading edge is proposed in combination with streamline tracing technique and blend function of osculating plane,with which the waveriders with hyper elliptic horizontal projection of leading edge(Waverider-F)and with hyper elliptic leading edge to hyper elliptic trailing edge transition(Waverider-FT)are designed.Both of them are of high volume ratio and their corresponding axial projection of leading edges is approximate to cosine curve.The effectiveness of the design method was validated by numerical simulation.For design point,Waverider-F has good waverider characteristics and keeps the feature of reference flow field.The forepart of Waverider-FT is a complete waverider,but the flow field is transfigured by both sides' induced shock of rear part and exists high pressure region.Their waverider characteristics are also good at relay point.Moreover,they are of high lift-drag ratio and pre-compression efficiency.Under inviscid condition,their life-drag ratios are 3.46 and 2.88 for design point.In comparison with Waverider-F,the lift force,drag force and exit compression ratio of Waverider-FT are significantly increased,and the lift-drag ratio,pitching moment and exit total pressure recovery coefficient are decreased.Under viscous condition,the lift-drag ratio at the design point decreases from 2.91 to 2.41,its corresponding exit total pressure recovery coefficient reduces 5.8%.

参考文献/References:

[1] 叶友达. 近空间高速飞行器气动特性研究与布局设计优化[J]. 力学进展, 2009, 39(6): 683-694.
[2] ANDERSON J D, LEWIS M J. Hypersonic waveriders: where do we stand?: AIAA 1993-0399 [R]. USA: AIAA, 1993.
[3] DUNCAN LUNAN M A. Waverider, a revised chronology: AIAA 2015-3529 [R]. USA: AIAA, 2015.
[4] NONWEILER T R F. Aerodynamic problems of manned space vehicles [J]. Journal of the royal aeronautical society, 1959, 63: 521-530.[5] JONES J U, MOORE K C,PIKE J, et al. A method for designing lifting configurations for high supersonic speeds using axisymmetric flow field [J]. Archive of applied mechanics, 1968, 37(1): 56-72.
[6] SOBIECZKY H, ZORES B, WANG Z. High speed flow design using the theory of osculating cones and axisymmetric flows [J]. Chinese journal of aeronautics, 1999, 12(1): 1-8.
[7] GOONKO Y P, MAZHUL I I, MARKELOV G N. Convergent flow derived waveriders [J]. Journal of aircraft, 2000, 37(4): 647-654.
[8] 李永洲,张堃元. 基于马赫数分布可控曲面外/内锥形基准流场的前体/进气道一体化设计[J] 航空学报,2015, 36(1): 289-301.
[9] RASMUSSEN M P. Waverider configurations derived from inclined circular and elliptic cones [J]. Journal of spacecraft and rockets, 1980, 17(5): 537-545.
[10] TAKASHIMA N, LEWIS M J. Waverider configurations based on non-axisymmetric flow fields for engine-airframe integration: AIAA 1994-0380 [R]. USA: AIAA, 1994.
[11] 刘传振,白 鹏,陈冰雁,等. 三维流场乘波体快速设计方法及多目标优化 [J]. 宇航学报, 2016, 37(5):535-543.
[12] LOBBIA M A, SUZUKIK. Multidisciplinary design optimization of hypersonic transport Configurations using waveriders: AIAA 2014-2359 [R]. USA: AIAA, 2014.
[13] OLSEN P E, NELSON R C. Vortex interaction over double delta wing at high angles of attack: AIAA 1989-2191 [R]. USA: AIAA, 1989.
[14] RODI P E. The osculating flowfield method of waverider geometry generation: AIAA 2005-0511 [R]. USA: AIAA, 2005.
[15] 段焰辉, 范召林, 吴文华. 定后掠角密切锥乘波体的生成和设计方法研究[J]. 航空学报, 2016, 37(10):3023-3034.
[16] 刘传振, 白鹏, 陈冰雁. 双后掠乘波体设计及性能优势分析[J]. 航空学报, 2017,38(6):120808.
[17] DRAYNA T W, NOMPELIS I, CANDLER G V. Hypersonic inward turning inlets: design and optimization: AIAA 2006-297 [R]. USA: AIAA, 2006.
[18] 李永洲,张堃元,孙迪. 马赫数可控的方转圆高超声速内收缩进气道实验研究[J]. 航空学报, 2016,37(10): 2970-2979.

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　LI Yongzhou,LI Guangxi,ZHANG Kunyuan,et al.Aerodynamic modification design and analysis of waverider with controllable leading and trailing edges[J].Journal of Rocket Propulsion,2018,44(05):1.

备注/Memo

收稿日期:2017-04-11; 修回日期:2017-05-17 基金项目:国家自然科学基金(11702205) 作者简介: 李永洲(1984—),男,博士,研究领域为高超声速组合发动机设计

更新日期/Last Update: 2017-11-10