RANS/LES在超声速突起物绕流中的应用研究

doi:10.7527/S1000-6893.2013.0271

Abstract

Abstract:

The protuberances fixed on a supersonic aircraft such as aerofoil or rudder may cause complex shock wave/boundary layer interactions which can greatly affect the aerodynamic characteristics around the protuberances or even in the whole aircraft. Traditional computational fluid dynamics (CFD) numerical methods solving Reynolds-averaged Navier-Stokes (RANS) equations cannot forecast the turbulence pulsating flow accurately. In this paper, a novel mixed RANS/LES (Large Eddy Simulation) model is developed based on the study of the merits and demerits of the B-L (Baldwin-Lomax) model and Smagorinsky model. Then it is applied to simulate the flow of the protuberances fixed on a rocket. Such flow phenomena as shock wave/boundary layer interaction, shear layer instability and separation vortex are depicted meticulously. The pressure pulsation process on the protuberance surface is obtained, and it is subsequently used to make a frequency spectrum analysis. Result indicates that the shock wave/boundary layer interaction rather than the bottom separation vortex is the main factor causing the pressure pulsation on the protuberance,. and this pressure vibration may affect badly the normal operation of the equipment in the rocket.

Key words: RANS/LES method, protuberance, shock wave/boundary layer interaction, supersonic flow, numerical simulation

CLC Number:

V411.4
O355

CHEN Qi, SI Fangfang, CHEN Jianqiang, YUAN Xianxu, XIE Yufei. Study of Protuberances in Supersonic Flow with RANS/LES Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(7): 1531-1537.

References

[1] Li S X. Complex flow field lead by shock wave and boundary layer. Beijing: Science Press, 2007: 11-15. (in Chinese) 李素循. 激波与边界层主导的复杂流动.北京:科学出版社, 2007: 11-15.

[2] Roshko A. Experiments on the flow past a circular cylinder at very high Reynolds number. Journal of Fluid Mechanics, 1961, 10(3): 345-356.

[3] Sedney R. A survey of the effects of small protuberance on boundary-layer flows. AIAA Jounal, 1973, 11(16): 782-792.

[4] Ozxan O, Holt M. Supersonic separate flow past a cylindrical obstacle on a flat plate. AIAA Journal, 1984, 22(5): 611-617.

[5] Bookey P, Wyckjam C, Smits A. Experiments investigations of Mach 3 shock-wave turbulent boundary layer interactions. AIAA-2005-4899, 2005.

[6] Estruch-Samper D, Bu X Q. Experimental investigation on hypersonic interference heating around surface protuberance. Acta Aeronautica et Astronautica Sinica, 2012, 33(9): 1578-1586.(in Chinese) Estruch-Samper D, 卜雪琴. 高超声速下表面凸起干扰气动热实验研究. 航空学报, 2012, 33(9): 1578-1586.

[7] Li S X. An experimental study and analysis on complex shock wave/boundary layer interactive flows induced by protuberances at hypersonic speed. Proceedings of the Eighth Asian Congress of Fluid Mechanics, 1999: 69-74.

[8] Herrin J L, Dutton J C. Base bleed experiments with a cylindrical after body in supersonic flow. Journal of Spacecraft Rockets, 1994, 31(6): 1021-1028.

[9] Roshko A. Experiments on the flow past a circular cylinder at very high Reynolds number. Journal of Fluid Mechanics, 1961, 10(3): 345-356.

[10] Shin J R, Cho D R, Won S H, et al. Hybrid RANS/LES study of base-bleed flows in supersonic mainstream. AIAA-2008-2588, 2008.

[11] Nichols R H. Comparison of hybrid RANS/LES turbulence models on a circular cylinder at high Reynolds number. AIAA-2005-498, 2005.

[12] Si F F. Study of the high speed main flow and thrust vectoring interaction. Mianyang: China Aerodynamics Research and Development Center, 2010.(in Chinese) 司芳芳. 推力转向喷流与高速主流干扰的数值模拟研究. 绵阳:中国空气动力研究与发展中心, 2010.

[13] Yuan X X, Deng X B, Xie Y F, et al. Research on the RANS/LES hybrid method for supersonic-hypersonic turbulence flow. Acta Aerodynamic Sinica, 2009, 27(6): 723-728. (in Chinese) 袁先旭,邓小兵,谢昱飞,等.超声速湍流流场的RANS/LES混合计算方法研究. 空气动力学学报, 2009, 27(6): 723-728.

[14] Kawai S, Fujii K. Compact scheme with filtering for large-eddy simulation of transitional boundary layer. AIAA Journal, 2008, 46(3): 690-700.

[15] Franck S, Sebastien D. Philippe G, et al. RANS-LES simulation of supersonic base flow. AIAA-2006-898, 2006.

Study of Protuberances in Supersonic Flow with RANS/LES Method

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	CHENG Jianrui, SHI Chongguang, QU Lixia, XU Yue, YOU Yancheng, ZHU Chengxiang. Theoretical model of 2D curved shock wave/turbulent boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(9): 125993-125993.
[2]	XIAHOU Tangfan, CHEN Jiangtao, SHAO Zhidong, WU Xiaojun, LIU Yu. Model validation metrics for CFD numerical simulation under aleatory and epistemic uncertainty [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(8): 25716-025716.
[3]	ZHANG Haoyuan, SUN Dong, QIU Bo, ZHU Yandan, WANG Anling. Influence of turbulent kinetic energy on shock wave/boundary layer interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 125504-125504.
[4]	YANG Jiankai, GU Dongdong, GE Qing, TAN Chenchen, WEN Yu. Support layout and precise forming mechanism of aluminum alloy for laser additive manufacturing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(4): 525331-525331.
[5]	JIANG Youxu, LI Jie, YANG Zhao. Data correction method of wind tunnel test for verification aircraft with laminar wing section [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526814-526814.
[6]	WANG Hao, ZHONG Min, HUA Jun, ZHONG Hai, YANG Tihao, WANG Meng, LEI Guodong. Simulation and experiment of natural laminar flow flight test wing glove [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526785-526785.
[7]	DUAN Junyi, TONG Fulin, LI Xinliang, LIU Hongwei. Decomposition of mean friction drag in compression-expansion turbulent boundary layer [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625915-625915.
[8]	SHEN Pengfei, LIU Pengxin, SUN Dong, YUAN Xianxu. Statistical characteristics of skin friction of shock wave/turbulent boundary layer interaction in hollow cylinder-flare configuration at Mach 6 [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626005-626005.
[9]	GANG Dundian, YI Shihe, MI Qi, NIU Haibo. Experiment on interaction between supersonic turbulent boundary layer and cylinder [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626104-626104.
[10]	XIE Zhuxuan, YANG Yanguang, WANG Gang. Structure of shock-induced separation in confined flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 626042-626042.
[11]	WANG Hongyu, YANG Yanguang, HU Weibo, CHEN Zhi, FENG Liming, ZHOU Youtian. Experimental study on unsteadiness characteristics of shock wave/turbulent boundary layer interaction controlled by high-frequency microsecond pulse discharge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625905-625905.
[12]	LIU Pengxin, YUAN Xianxu, LIANG Fei, LI Chen, SUN Dong. Quadrant decomposition analysis of fluctuations in high-temperature turbulent boundary layer with chemical non-equilibrium [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726338-726338.
[13]	BAO Jun, WANG Yu, NIU Qian, ZHU Xidong, CHENG Jianjie. Influencing parameters and film flow mechanism of spray droplet impacting liquid film [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726360-726360.
[14]	CHEN Chongpei, LIANG Jianhan, GUAN Qingdi, GAO Tianyun. Conservative compressible one-dimensional turbulence method and its application in supersonic scalar mixing layer [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726364-726364.
[15]	LI Qing, TU Guohua, YU Zhaosheng, LIN Zhaowu, LI Tingting, YUAN Xianxu. Inertial particle transport in non-uniform accelerated flow [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726390-726390.