展向宽度对激波入射平板反射类型的影响

doi:10.7527/S1000-6893.2021.25927

Abstract

Abstract: Shock wave interference is a local interference phenomenon that needs to be considered in the pneumatic layout of hypersonic vehicle and the design of scramjet. When this phenomenon occurs, complex wave structures will be generated to affect the behavior characteristics of the flow field and then significantly affect the planeload and engine performance. Numerical simulation is used to study the problem of incident shock wave of a plate. Under the condition of constant Mach number 5 and unit Reynolds number 7.12×10⁶ m^-1, the types of shock reflection in six different states are studied by changing the transverse width of the upper and lower plates. The results show that the influence of lateral overflow on the reflection types of shock wave must be considered in the restricted space. With the broadening of the transverse width of the plate, the shock reflection type gradually changes from regular reflection to Mach reflection, and the length of Mach stem becomes longer and moves forward gradually until the inner channel is blocked and the detached shock wave is formed. The shock polar theory is also used to analyze the generation mechanism of the two shock interference types under the condition of a fixed shock angle. The analysis shows that with the increase of shock wave intensity, the two transmission shock pole curves move upward and shrink, which leads to the requirement for parameter matching of the flow field behind the wave. The shock reflection type gradually changes from regular reflection to Mach reflection, and the conclusion is consistent with the numerical calculation and wind tunnel test results.

Key words: transverse width, regular reflection, Mach reflection, shock polar curve, wind tunnel test

CLC Number:

V411

ZHANG Zhigang, ZHAO Jinshan, WANG Chengpeng, LUO Wanqing, LIAO Junhao, XIAO Yu, CHEN Ting, SU Siyao. Influence of spanwise width on reflection types of oblique shock wave incident plate[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 625927.

References

[1] 田正雨, 李桦, 范晓樯. 六类高超声速激波-激波干扰的数值模拟研究[J]. 空气动力学学报, 2004, 22(3): 361-364. TIAN Z Y, LI H, FAN X Q. Numerical investigation for six types of hypersonic turbulent shock-shock interaction[J]. Acta Aerodynamica Sinica, 2004, 22(3): 361-364(in Chinese).
[2] MACH E. Uber den verlauf von funkenwellen in der ebene und im raume[J]. Sitzungsbr Akad Wiss Wien, 1878, 78: 819-838. MACH E. On the course of spark waves in the plane and in space[J]. Sitzungsbr Akad Wiss Wien, 1878, 78: 819-838(in German).
[3] HOLGER B, JOHN K H. 激波边界层干扰[M]. 白菡尘, 译. 北京: 国防工业出版社, 2015: 5-71. HOLGER B, JOHN K H. Shock wave-boundary-layer interactions[M]. BAI H C, translated. Beijing: National Defense Industry Press, 2015: 5-71(in Chinese).
[4] VON NEUMANN J. Oblique reflection of shock[J]. John von Neumann Collected Works, 1943, 6: 238-299.
[5] VON NEUMANN J. Refraction, intersection and reflection of shock waves: NAVORD Report No.203-245[R]. Washington, D.C.: Navy Department, 1945.
[6] BEN-DOR G, IVANOV M, VASILEV E I, et al. Hysteresis processes in the regular reflection?Mach reflection transition in steady flows[J]. Progress in Aerospace Sciences, 2002, 38(4-5): 347-387.
[7] BEN-DOR G. Shock wave reflections in steady flows[M]//Shock Wave Reflection Phenomena. New York: Springer New York, 1992: 175-199.
[8] CHPOUN A, PASSEREL D, LI H, et al. Reconsideration of oblique shock wave reflections in steady flows. Part 1. Experimental investigation[J]. Journal of Fluid Mechanics, 1995, 301: 19-35.
[9] CHPOUN A, PASSEREL D, LENGRAND J C, et al. Mise en evidence experimental et numericale d’unphenomene d’hysteresis lors de la transition reflexion de Mach-reflexion reguliere[J]. Comptes Rendus de l Académie des Sciences-Series IIB-Mechanics, 1994, 319(12): 1447-1453. CHPOUN A, PASSEREL D, LENGRAND J C, et al. Experimental and numerical demonstration of a hysteresis phenomenon during the transition from Mach reflection to regular reflection[J]. Accounts of the Academy of Sciences-Series IIB-Mechanics, 1994, 319(12): 1447-1453(in French).
[10] IVANOV M, ZEITOUN D, VUILLON J, et al. Investigation of the hysteresis phenomena in steady shock reflection using kinetic and continuum methods[J]. Shock Waves, 1996, 5(6): 341-346.
[11] SHIROZU T, NISHIDA M. Numerical studies of oblique shock reflection in steady two dimensional flows[J]. Memoirs of the Faculty of Engineering KYUSHU University, 1995, 55(2): 193-204.
[12] KUDRYAVTSEV A N, KHOTYANOVSKY D V, MARKELOV G N, et al. Numerical simulation of reflection of shock waves generated by finite-width wedge[C]//Proceedings of the 22nd International Symposium Shock Waves, Vol.2.Southampton: University of Southampton, 1999: 1185-1190.
[13] IVANOV M S, BEN-DOR G, ELPERIN T, et al. Flow-Mach-number-variation-induced hysteresis in steady shock wave reflections[J]. AIAA Journal, 2001, 39(5): 972-974.
[14] ONOFRI M, NASUTI F. Theoretical considerations on shock reflections and their implications on the evaluation of air intake performance[J]. Shock Waves, 2001, 11(2): 151-156.
[15] ZHANG E L, LI Z F, LI Y M, et al. Three-dimensional shock interactions and vortices on a V-shaped blunt leading edge[J]. Physics of Fluids, 2019, 31(8): 086102.
[16] 张恩来, 李祝飞, 杨基明. 三维激波反射理论与数值研究[C]//首届全国空气动力学大会论文集. 绵阳: 中国空气动力研究与发展中心, 2018: 1-7. ZHANG E L, LI Z F, YANG J M. Three-dimensional shock reflection theory and numerical research[C]//Proceedings of the First National Aerodynamics Conference. Mianyang: China Aerodynamics Research and Development Center, 2018: 1-7(in Chinese).
[17] 张恩来. 高超声速内外流中的三维激波相互作用[D]. 合肥: 中国科学技术大学, 2019. ZHANG E L. Three-dimensional shock interactions inhypersonic internal/external integration flows[D]. Hefei: University of Science and Technology of China, 2019(in Chinese).
[18] 谭廉华. 平面与轴对称定常激波马赫反射中的激波形状研究[D]. 北京: 清华大学, 2007. TAN L H. On the shape of shock waves in steady planar and axisymmetical Mach reflections[D]. Beijing: Tsinghua University, 2007(in Chinese).
[19] TAN L H, REN Y X, WU Z N. Analytical and numerical study of the near flow field and shape of the Mach stem in steady flows[J]. Journal of Fluid Mechanics, 2006, 546: 341-362.
[20] REN Y X, TAN L H, WU Z N. The shape of incident shock wave in steady axisymmetric conical Mach reflection[J]. Advances in Aerodynamics, 2020, 2(1): 474-484.
[21] 傅德薰, 马延文. 计算流体力学[M]. 北京: 高等教育出版社, 2002. FU D X, MA Y W. Computational fluid dynamics[M]. Beijing: Higher Education Press, 2002(in Chinese).
[22] STEGER J L, WARMING R F. Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods[J]. Journal of Computational Physics, 1981, 40(2): 263-293.
[23] TORO E F. Riemann solvers and numerical methods for fluid dynamics[M]//The Riemann Problem for the Euler Equations. Berlin: Springer, 1997: 115-157.
[24] 黎作武. 近似黎曼解对高超声速气动热计算的影响研究[J]. 力学学报, 2008, 40(1): 19-25. LI Z W. Study on the dissipative effect of approximate Riemann solver on hypersonic heatflux simulation[J]. Chinese Journal of Theoretical and Applied Mechanics, 2008, 40(1): 19-25(in Chinese).
[25] YOON S, JAMESON A. Lower-upper symmetric-Gauss-Seidel method for the Euler and Navier-Stokes equations[J]. AIAA Journal, 1988, 26(9): 1025-1026.

Influence of spanwise width on reflection types of oblique shock wave incident plate

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	Pengpeng SUN, Ping’an LIU, Feng FAN, Wei ZENG. Aerodynamic interaction characteristics of coaxial rigid rotor⁃fuselage in hover condition [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529284-529284.
[2]	Chang WANG, Long HE, Dongxia XU, Min TANG, Shuai MA, Ximing WU. Flow control drag reduction of hub on coaxial rigid rotor aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529084-529084.
[3]	Weiguo ZHANG, Min TANG, Jie WU, Xianmin PENG, Guichuan ZHANG, Bowen NIE, Liangquan WANG, Chaoqun LI. Overview of wind tunnel test research on tiltrotor aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 530114-530114.
[4]	Bowen NIE, Liangquan WANG, Zhiyin HUANG, Long HE, Shipeng YANG, Hongtao YAN, Guichuan ZHANG. Flight dynamics modeling and control scheme design of compound high-speed unmanned helicopters [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 529848-529848.
[5]	Qichang CHEN, Zhiwei SHI, Weiyuan ZHANG, Linglong YAO, Shengxiang TONG. Aerodynamic layout and control strategy design and flight verification of a wing⁃foldable variant VTOL aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629583-629583.
[6]	Liu LIU, Xianhong XIANG, Yufei ZHANG, Haixin CHEN, Chuang WEI, Jian ZHU, Pu YANG. A high lift-to-drag ratio unconventional blended-wing-body aerodynamic configuration with swallow tail [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(6): 629630-629630.
[7]	Haixing LI, Feng ZHOU, Wei YAN, Feng BAI, Keliang ZHAO. Effects of roughness ice on aerodynamic performance of civil aircraft horizontal tail [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128657-128657.
[8]	Yu LIU, Mengjie QIN, Qiang WANG, Xian YI. Scaling law for salty sea spray icing wind tunnel test [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729297-729297.
[9]	Qiuming YANG, Yongfeng ZHU, Huawei CHEN, Xiaolin LIU. Anti-icing performance test investigation on hollowed patterning electric heating module [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729334-729334.
[10]	Shiqi GAO, Bo DING, Xuzhen XIE, Zheng LI, Lin CHEN, Shouyuan QIAN, Zihan JIAO, Guanghui BAI. Drag reduction mechanism using plasma synthetic jet in high⁃speed flow [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729373-729373.
[11]	Lingsong XU, Yuan WU, Dongyu ZHU, Fukun ZHANG, Yu LIU. A wing pitch oscillation mechanism for FL⁃61 icing wind tunnel [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S2): 729296-729296.
[12]	Yi JIN, Shu SUN, Yunjie GUO, Huijun TAN, Yue ZHANG. Dual solution internal flow phenomenon and throttling characteristics of a supersonic variable inlet [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 127134-127134.
[13]	Junhong LI, Xuhong JIN, Chunfeng LIU, Wenbo MIAO, Xiaoli CHENG. Microaerodynamic experiment and computation of near space high speed vehicles [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 127072-127072.
[14]	Xian’ang ZENG, Dongqiang ZHAO, Junjie LI, Zezhou YAN, Chengyu LIU. Wind tunnel test on gust alleviation control strategies of elastic wing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(4): 226869-226869.
[15]	Chang LIU, Yunlong ZHANG, Zhijiang YAN, Lei ZHAO, Chen JI. Wind tunnel test of fluctuating pressure on aeroelastic scaled model of hammerhead launch vehicle [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 128384-128384.