三维内收缩式进气道V形溢流口热流计算与分析

推进技术 ›› 2018, Vol. 39 ›› Issue (8): 1737-1743.

三维内收缩式进气道V形溢流口热流计算与分析

蒙泽威,范晓樯,陶渊,陆雷

国防科技大学航天科学与工程学院，湖南长沙 410073,国防科技大学航天科学与工程学院，湖南长沙 410073,国防科技大学航天科学与工程学院，湖南长沙 410073,国防科技大学航天科学与工程学院，湖南长沙 410073

发布日期:2021-08-15
基金资助:
国家自然科学基金(11572347；11372347)。

Investigation of Aerothermal Heating on V-Shaped Leading Edge of Inward Turning Inlet

College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China,College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China,College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China and College of Aerospace Science and Engineering，National University of Defense Technology，Changsha 410073，China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得流场特性和热流影响规律，将高超声速进气道中带有V形的溢流口进行简化，采用数值计算和实验相结合的方法研究了简化后V形溢流口的前缘热流，对比分析了不同前缘钝化构型、不同前缘角θ以及不同倒圆半径比R/r下V形溢流口的热流分布。结果表明，和钝头体以及旋成体相比，钝化的V形溢流口受到更加严重的热载荷，流场结构也更加复杂；改变前缘角θ并不能显著降低热流，可见通过改变前缘角θ对溢流口前缘热流改善能力有限；倒圆半径比R/r对V形溢流口热流影响明显，倒圆半径比R/r<6时，溢流口前缘气动受热剧烈，倒圆半径比R/r>6时，热流峰值降低且随倒圆半径比R/r变化不明显。在进气道设计中应综合考虑气动性能和热防护等因素进行合理取舍。

关键词: V形溢流口；热流；内收缩进气道

Abstract: In order to obtain the flow field characteristics and the influence of aerothermal heating，the cowl of hypersonic inward turning inlet is simplified as V-shaped leading edge. By means of numerical simulations and wind tunnel tests，the simplified model is studied with different blunt configurations，angle (θ) of leading edge and ratio (R/r) of rounding radius and blunt radius. The results show that，comparing with blunt body and slender body，the V-shaped leading edge exists complex shock wave interference and suffers critical aerothermal heating. The heat flux reduces slightly and the peak value of it still keeps high level when angle is changed. In other words，it is limited to achieve thermal protection by changing angle of leading edge. The ratio of rounding radius and blunt radius impacts significantly the aerothermal heating of V-shaped leading edge. With increasing of ratio，the peak value of heat flux decreases significantly. Heat flux keeps greatly high level when R/r<6 and Heat flux keeps steady low level when R/r>6. Multi-factor，including aerodynamic performance and thermal protection，should be taken into account and be made a reasonable choice for designing in hypersonic inlet.

Key words: V-shaped leading edge；Heat flux；Inward turning inlet

蒙泽威,范晓樯,陶渊,陆雷. 三维内收缩式进气道V形溢流口热流计算与分析[J]. 推进技术, 2018, 39(8): 1737-1743.

MENG Ze-wei,FAN Xiao-qiang,TAO Yuan,LU Lei. Investigation of Aerothermal Heating on V-Shaped Leading Edge of Inward Turning Inlet[J]. Journal of Propulsion Technology, 2018, 39(8): 1737-1743.

参考文献

[1] 王哲, 李旭昌. 高超声速三维内收缩式进气道研究进展[J]. 飞航导弹, 2014, 4: 79-87.
[2] 吴颖川, 贺元元, 贺伟, 等. 吸气式高超声速飞行器机体推进一体化技术研究进展[J]. 航空学报, 2015, 36(1): 245-260.
[3] 尤延铖, 梁德旺, 郭荣伟. 高超声速三维内压缩式进气道/乘波前体一体化设计研究评述[J]. 力学进展, 2009, 39(5): 513-525.
[4] Billig F S. Design and Analysis of Streamline Traced Hypersonic Inlets[C]. Norfolk: 9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999.
[5] Billig F S. Streamline Tracing: Technique for Designing Hypersonic Vehicles[J]. Journal of Propulsion and Power, 2000, 16(3): 465-471.
[6] Malo-Molina F J, Gaitonde D V. Numerical Investigation of an Innovative Inward Turning Inlet[C]. Toronto: 17th AIAA Computational Fluid Dynamics Conference, 2005.
[7] 尤延铖, 梁德旺. 基于内乘波概念的三维变截面高超声速进气道[J]. 中国科学, 2009, 39(8): 1483-1494.
[8] Smart M K. Experimental Testing of a Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition[J]. Journal of Propulsion and Power, 2001, 17(2): 276-283.
[9] Smart K M, Trexler A C. Mach 4 Performance of Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition[J]. Journal of Propulsion and Power, 2004, 20(4): 288-292.
[10] Walker H S. Hypersonic Collaborative Australia/United States Experiment (HYCAUSE)[R]. AIAA 2005-3254.
[11] Tam C J, Robert A B, Gary D S. Numerical Analysis of Streamline-Traced Hypersonic Inlets[R]. AIAA 2003-13.
[12] 孙波, 张堃元. Busemann进气道起动问题初步研究[J]. 推进技术, 2006, 27(2): 128-131. (SUN Bo, ZHANG Kun-yuan. Preliminary Investigation on Busemann Inlet Starting Characteristics[J]. Journal of Propulsion Technology, 2006, 27(2): 128-131.)
[13] 潘瑾, 张堃元. 可变内收缩比侧压式进气道自起动性能[J]. 推进技术, 2007, 28(3): 278-281. (PAN Jin, ZHANG Kun-yuan. Self-Starting Characteristics for Sidewall-Compression Inlet with Variable Internal Contraction Ratio[J]. Journal of Propulsion Technology, 2007, 28(3): 278-282.)
[14] 金志光, 张堃元. 高超侧压式进气道简单唇口调节方案设计[J]. 推进技术, 2008, 29(1): 43-48. (JIN Zhi-guang, ZHANG Kun-yuan. Concept of a Varied Geometry Scramjet Inlet with Rotatable Cowl[J]. Journal of Propulsion Technology, 2008, 29(1), 43-48.)
[15] 肖丰收. 若干典型高超声速激波干扰流动特性研究 [D]. 合肥:中国科学技术大学, 2016.
[16] Duquesne N, Roquefort TAd. Numerical Investigation of a Three-Dimensional Turbulent Shock/Shock Interaction[R]. AIAA 98-0774.
[17] 潘沙, 田正雨, 冯定华. 超燃冲压发动机唇口气动热计算研究与分析[J]. 航空动力学报, 2009, 24(9): 2096-2100.
[18] Curran E T , Murthy S N B . Scramjet Propulsion[M]. New York: American Institute of Aeronautics and Astronautics Inc, 2000.
[19] 贺旭照, 赵慧勇, 乐嘉陵. 吸气式高超声速飞行器气动力气动热的数值模拟方法及应用[J]. 计算物理, 2008 , 25(5): 555-560.
[20] 张志雨, 肖丰收. 钝化V形前缘激波干扰特性研究[C]. 成都:第十七届全国激波与激波管学术会议, 2016.(编辑:张荣莉)　　　　　　　　　　　　　*　收稿日期:2017-07-15；修订日期:2017-09-11。基金项目:国家自然科学基金(11572347；11372347)。通讯作者:蒙泽威,男,硕士生,研究领域为高超声速推进技术。E-mail: mengzw94@163.com