圆截面超燃冲压发动机冷态内流测力试验

推进技术 ›› 2016, Vol. 37 ›› Issue (4): 617-623.

圆截面超燃冲压发动机冷态内流测力试验

王泽江¹,唐小伟²,宋文萍¹,张勇²

西北工业大学航空学院，陕西西安 710072,中国空气动力研究与发展中心，四川绵阳 6210002,西北工业大学航空学院，陕西西安 710072,中国空气动力研究与发展中心，四川绵阳 6210002

发布日期:2021-08-15
作者简介:王泽江，男，博士生，副研究员，研究领域为高超声速空气动力学。

Zero-Fuel Internal Flow Force Test for Circular Cross Section Scramjet Engine

School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China,China Aerodynamic Research and Development Center，Mianyang 621000，China,School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China and China Aerodynamic Research and Development Center，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 不论是超燃冲压发动机推进性能评估，还是吸气式高超声速飞行器气动性能预测，冷态内流气动性能至关重要。为验证冷态内流测力新技术，以采用Nose-to-Tail力核算方法的圆截面超燃冲压发动机为试验对象，在马赫数6条件下开展了风洞试验，并将试验测量结果与基于动量定理的CV2预测方法的内阻评估值进行了对比。结果表明，采用天平直接测量发动机冷态内流气动力载荷的试验方法可行。测量结果可信度高；重复性好，进气道起动时的相对误差约4%；精度高，可控制在3%左右；试验信息丰富，能够直观真实地反映内流气动性能、进气道起动/不起动、溢流等物理现象。

关键词: 高超声速；风洞试验；超燃冲压发动机；内流气动力；应变天平；阻力

Abstract: The zero-fuel internal aerodynamic force is significant not only to the scramjet engine thrust performance evaluation but also to the air-breathing hypersonic vehicle aerodynamic performance prediction. A new experimental technique was developed for zero-fuel internal flow force testing. The wind tunnel test at Mach 6 was carried on with a certain circular cross section scramjet engine，and the test results were compared with the internal drag evaluated by the control volume method CV2 based on the theorem of momentum according to the nose-tail force accounting strategy. The results show that the technique for direct-measuring the aerodynamic loads on scramjet engine zero-fuel internal flow by strain-gauge balance is feasible，whose measurement have many advantages，such as high creditability，good reproducibility with the relative error about 4% in the case of inlet staring，high accuracy with the measurement error is within about 3%，abundant information amount，capability of visually and actually reflecting the physical phenomena of internal aerodynamic performance，inlet starting or un-starting and spillage and so on.

Key words: Hypersonic；Wind tunnel test；Scramjet engine；Internal aerodynamic；Strain-gauge balance; Drag

王泽江,唐小伟,宋文萍,张勇. 圆截面超燃冲压发动机冷态内流测力试验[J]. 推进技术, 2016, 37(4): 617-623.

WANG Ze-jiang¹,TANG Xiao-wei²,SONG Wen-ping¹,ZHANG Yong². Zero-Fuel Internal Flow Force Test for Circular Cross Section Scramjet Engine[J]. Journal of Propulsion Technology, 2016, 37(4): 617-623.

参考文献

[1] Holland S D, Woods W C, Engelund W C. Hyper-X Research Vehicle Experimental Aerodynamics Test Program Overview[J]. Journal of Spacecraft and Rockets, 2001, 38(6): 11-12.
[2] Engelund W C, Holland S D, Charles E. Aerodynamic Database Development for the Hyper-X Airframe Integrated Scramjet Propulsion Experiments[R]. AIAA 2000-4006.
[3] Wang W X, Guo R W. Numerical Study of Unsteady Starting Characteristics of a Hypersonic Inlet[J]. Chinese Journal of Aeronautics, 2013, 26(3): 563-571.
[4] Sun S, Zhang H Y, Cheng K M, et al. The Full Flowpath Analysis of a Hypersonic Vehicle[J]. Journal of Astronautics, 2007, 20: 385-393.
[5] Anderson G Y, Mackley E A. Mach 7 Performance of the Langley Airframe-Integrated Modular Scramjet[C]. USA: JANNAF Propulsion Meeting, CPIA Pub, 1983.
[6] Voland R T. Methods for Determining the Internal Thrust of Scramjet Engine Modules from Experimental Data[R]. AIAA 90-2340.
[7] Kitamura E, Mitani T, Sakuranaka N, et al. Evaluating the Aerodynamic Performance of Scramjet Engines by Pressure Measurement[R]. AIAA 2003-7053.
[8] Kouchi T, Mitani T, Hiraiwa T, et al. Evaluation of Thrust Performance in Scramjet Engines with Measured Internal Drag [J]. Journal of the Japan Society for Aeronautical and Space Sciences, 2003, 51(595): 403-411.
[9] Shimura T, Sakuranaka N, Sunami T, et al. Lift and Pitching Moment of a Scramjet Engines [J]. Journal of Propulsion and Power, 2001, 17(3): 617-621.
[10] 李俊红, 程晓丽, 沈清. 超燃冲压发动机性能预测工程方法. 推进技术[J], 2009, 30(2): 129-134, 164. (LI Jun-hong, CHENG Xiao-li, SHEN Qing. Engineering Method of Scramjet Engine Performance Prediction Based on Nozzle Exit Pressure[J]. Journal of Propulsion Technology, 2009, 30(2): 129-134, 164.)
[11] 许晓斌, 舒海峰, 谢飞, 等. 通气模型内流道阻力直接测量技术[J]. 推进技术, 2013, 34(3): 311-315. (XU Xiao-bin, SHU Hai-feng, XIE Fei, et al. Technique Investigation on Flow Through Model Inner Flow Drag Straightway Measured by Strain-Gauge Balance[J]. Journal of Propulsion Technology, 2013, 34(2): 311-315.)
[12] 王泽江, 李绪国, 孙鹏, 等. 高超声速内外流解耦试验系统设计与验证[J]. 推进技术, 2015, 36(6): 920-926. (WANG Ze-jiang, LI Xu-guo, SUN Peng, et al. Design and Verification for Hypersonic Aerodynamic Test System of Internal Flow and External Flow Decoupling[J]. Journal of Propulsion Technology, 2015, 36(6): 920-926.)
[13] 王泽江, 孙鹏, 李绪国, 等. 吸气式高超声速飞行器内外流同时测力试验[J]. 航空学报, 2015, 36(3): 797-803.
[14] 恽起麟. 实验空气动力学[M]. 北京:国防工业出版社, 1991: 252-260.
[15] 王发祥. 高速风洞试验[M]. 北京:国防工业出版社, 1999: 204-218, 248-249.
[16] Olsen J A. Spillage Drag Estimation and Drag-Thrust Accounting for a Missile with Air Breathing Propulsion[D]. Stockholm, Sweden: Department of Aerospace, Royal Institute of Technology, 2012.
[17] 赵一龙, 范晓樯, 王翼, 等. 高超侧压进气道溢流方案的改进与分析[J]. 推进技术, 2013, 34(7): 873-879. (ZHAO Yi-long, FAN Xiao-qiang, WANG Yi, et al. Spillage Amelioration and Analysis of Side-Compression Hypersonic Inlet[J]. Journal of Propulsion Technology, 2013, 34(7): 873-879.)
[18] 骆晓臣, 张堃元. 侧压式进气道附加阻力分析[J]. 推进技术, 2007, 28(6): 624-628. (LUO Xiao-chen, ZHANG Kun-yuan. Analysis of Additive Drag in SideWall Compression Inlet[J]. Journal of Propulsion Technology, 2007, 28(6): 624-628.)
[19] 唐志共. 高超声速气动力试验[M]. 北京:国防工业出版社, 2004:75-77, 257-259.
[20] 路波. 高速风洞测力试验数据处理方法[M]. 北京:国防工业出版社, 2014: 115-116.*　收稿日期:2014-11-21；修订日期:2015-02-05。作者简介:王泽江,男,博士生,副研究员,研究领域为高超声速空气动力学。E-mail: wangpeiyi1209@163.com(编辑:史亚红)