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孙波
2023-05-22 15:07
  • 孙波
  • 孙波 - 硕士生导师-南京理工大学-机械工程学院-个人资料

近期热点

资料介绍

个人简历


2011.05-2012.05 德国亚琛工业大学 访问学者

研究领域


1、高超声速飞行器进气道一体化设计;
2、组合循环发动机进气系统设计;
3. 再入飞行器气动力/气动热数值模拟.""

近期论文


Chunliang Dai, Bo Sun∗, Shengbing Zhou, et al . Influence of high temperature non-equilibrium effects on Mach 12 scramjet inlet. Acta Astronautica 193 (2022) 237–254.
Chunliang Dai, Bo Sun∗, Changsheng Zhou, et al . Numerical investigation of real-gas effect of inward-turning inlet at Mach12. Aerospace Science and Technology,115 (2021):106786.
孙波,卓长飞. 内流激波边界层干扰非对称特性研究综述[J]. 气动研究与实验, 2021, 33(04): 15-22.
王海,孙波*,卓长飞,满延进,李宏东. 预冷发动机进气道节流特性数值研究. 航空动力学报. 2021,36(03).
杜磊,孙波*,代春良,卓长飞. 壁面温度对斜爆震发动机进气道流动特性影响的数值研究. 推进技术. 2021,42(04).
代春良,孙波,梁晓扬,卓长飞,张堃元.真实气体效应下高马赫数内转进气道特性研究.推进技术,2020.
Sun, B.; Wang, C.; Zhuo, C. Theoretical Model and Numerical Analysis for Asymmetry of Shock Train in Supersonic Flows. Symmetry 2020, 12, 518. SCIE
SUN Bo,XIANG Cuiling,ZHUO Changfei. Back Pressure Characteristics for Turbine Channel of External?Parallel TBCC Inlet. Transactions of Nanjing University of Aeronautics and Astronautics,2019,36(5):808?816.
代春良,孙波*,张堃元.马赫数3~6宽速域内转进气道优化设计.航空动力学报,2019, 34(10).
闵浩,孙波,李嘉新,邬凤林,张堃元.一种内并联型内转进气道通道间干扰特性研究.推进技术,2018,39(12).
Xiaoqian Chen, Bo Sun*, Chunliang Dai, and Xiangang Wang. Wind energy harvesting using jet-edge flow oscillations. AIP Advances,2018,8, 095018.SCI
Luo Xiaochen, Sun Bo*, Wang Xiang'ang. Experimental investigation on a cavity-step-actuated supersonic oscillating jet. Chinese Journal of Aeronautics, 2017, 30(1): 274–281.SCI
孙波,邵庆龄,倪凯捷,卓长飞,张堃元.并联TBCC可调进气道并联方案.航空动力学报,2017,32(12).EI
Bo Sun, Feng Feng, Xiao-song Wu, Xiao-chen Luo*. Experimental Investigations of Cavity-actuated Supersonic Oscillating Jet. Experimental Thermal and Fluid Science,2015, 68: 155-162.( SCIE: 000365361800015, JCR:3区,IF:1.99)
Bo Sun, Xiao-chen Luo*,Feng Feng, Xiao-song Wu. Experimental investigation on cavity-actuated under-expanded supersonic oscillating jet, 2015, 28(5): 1372–1380.( SCIE: 000367071000007,JCR:4区,IF:1.07)
南向军,张堃元*,金志光,孙波. 矩形转圆形高超声速内收缩进气道数值及实验研究.航空学报,第32卷,第6期,988-996页, 2011. (EI: 20112814137367)
南向军, 张堃元*, 金志光, 孙波. 压升规律可控的高超声速内收缩进气道设计. 航空动力学报,第26卷,第3期,518-523页,2011. (EI: 20112013987438)
Sun B, Zhang K Y*. Empirical Equation for Self-Starting Limit of Supersonic Inlets. Journal of Propulsion and Power, Vol. 26, No.4, pp. 874-875, 2010. (SCI: 000280255300028)
Sun B, Zhang K Y*, Wang C P, and Wu X S. Investigation on a Streamtraced Hypersonic Busemann Inlet. Proc. IMechE, Part G: J. Aerospace Engineering, Vol. 224, No. G1, pp.57-63, 2010. (SCIE: 000273895700005)
孙波,张堃元,武晓松. 弹用模块化Busemann进气道数值研究[J]. 航空动力学报, 2009,24(3):573-580. (EI: 20091612036304)
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