An Investigation of Fluctuating Pressure Environment around Rocket Fairing with Different Curvetypes

doi:10.3969/j.issn.1000-1093.2017.05.023

Abstract

Abstract: The surface fluctuating pressure environments of the rocket fairings with different curve types, namely normal spherically blunted cone, power series cone and von Karman cone, are systematically investigated by large-eddy simulations (LES). For all the three curve types, the peak of fluctuating pressure is found at a region where shock/separation bubble interacts at a transonic Mach number. The location of the maximum value is consistent with the time-averaged station of shocks. Compared with the fluctuating pressure environment of normal spherically blunted cone, the range and peak of root-mean square pressure coefficient C_{p_rms} are diminished, with the peak value being decreased by 17% for both power series cone and von Karman cone. In particular, serious fluctuating environment could also be induced by the expansion fan, where significant flow acceleration and deceleration occur. The reattached turbulent boundary-layer develops more quickly for normal spherically blunted cone, with its noise magnitude being 10 dB larger than others. Key

Key words: basicdisciplinesofaerospacescienceandtechnology, rocketfairing, curvetype, fluctuatingpressure, large-eddysimulation, aeroacoustic

CLC Number:

V411.4

ZHAO Rui, RONG Ji-li, LI Yue-jun, LI Hai-bo. An Investigation of Fluctuating Pressure Environment around Rocket Fairing with Different Curvetypes[J]. Acta Armamentarii, 2017, 38(5): 1020-1026.

References

［1］ Rainey G. Progress on the launch-vehicle buffeting problem [J]. Journal of Spacecraft and Rockets, 1965, 2(3): 289-299.
[2] 唐伟, 江定武, 桂业伟, 等. 旋成体导弹头部母线线性的选择问题研究[J]. 空气动力学学报, 2010, 28(2): 218-221.
TANG Wei, JIANG Ding-wu, GUI Ye-wei, et al. Study on generatrix curvetypes of axis-symmetric missiles [J]. Acta Aerodynamica Sinica, 2010, 28(2): 218-221. (in Chinese)
[3] Perkins E W, Jorgensen L H. Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 3.67, A52H28[R]. US:NACA, 1952.
[4] Stoney Jr WE. Transonic drag measurements of eight-body nose shapes, L53K17[R]. US: NACA, 1954.
[5] Perkins E W, Jorgensen L H, Sommer S C. Investigation of the drag of various axially symmetric nose shapes of fineness ratio 3 for Mach numbers from 1.24 to 7.4, A52H28[R]. US:NACA, 1958.
[6] Lee J W, Min B Y, Byun Y H, et al. Multi-point nose shape optimization of space launcher using response surface method[C]∥40th AIAA Aerospace Sciences Meeting & Exhibit. Reno, NV, US:AIAA, 2002: 2002-0106.
[7] Gusman M R, Housman J A, Kiris C C. Adjoint-based adaptive meshing in a shape trade study for rocket ascent[C]∥6th International Conference on Computational Fluid Dynamics (ICCFD6). St Petersburg, Russia:Springer, 2010: 391-400.
[8] Engblom W A. Numerical simulation of Titan IVB transonic buffet environment[J]. Journal of Spacecraft and Rockets, 2003, 40(5): 648-656.
[9] Tsutsumi S, Takaki R, Takama Y, et al. Hybrid LES/RANS simulations of transonic flowfield around a rocket fairing[C]∥30th AIAA Applied Aerodynamics Conference. New Orleans, LA, US:AIAA, 2012: 2012-2900.

[10] Brauckmann G J, Streett C L, Kleb W L, et al. Computational and experimental unsteady pressures for alternate SLS booster nose shapes[C]∥AIAA, Aerospace Sciences Meeting. Kissimmee, FL, US: AIAA, 2015: 2015-0559.
[11] 赵瑞, 荣吉利, 任方, 等. 火箭整流罩外气动噪声环境的大涡模拟研究[J].宇航学报, 2015, 36(9) : 988-994.
ZHAO Rui, RONG Ji-li, REN Fang, et al. Large eddy simulation of the aeroacoustic environment of a rocket fairing[J]. Journal of Astronautics, 2015, 36(9): 988-994. (in Chinese)

[12] 赵瑞, 荣吉利, 任方, 等. 一种改进的跨声速旋成体壁面脉动压力预测方法[J]. 宇航学报, 2016, 37(10):1179-1184.
ZHAO Rui, RONG Ji-li, REN Fang, et al. Improvement of the fluctuating pressure empirical functions around rotated aircraft at transonic Mach numbers[J]. Journal of Astronautics, 2016, 37(10): 1179-1184. (in Chinese)
[13] Matsukawa Y. Implicit large eddy simulation of a supersonic flat-plate boundary layer flow by weighted compact nonlinear scheme[J]. International Journal of Computational Fluid Dynamic, 2011, 25(2): 47-57.
[14] Shen Y Q, Zha G C, Chen X Y. High order conservative differencing for viscous terms and the application to vortex-induced vibration flows [J]. Journal of Computational Physics, 2008, 228(22): 8283-8300.
[15] Dubuc L, Cantariti F, Woodgate M, et al. Solution of unsteady Euler equations using an implicit dual time step method [J]. AIAA Journal, 1998, 36(8): 1417-1424.
[16] Jameson A, Yoon S. Lower-upper implicit schemes with multiple grids for the Euler equations[J]. AIAA Journal, 1987, 25(7): 929-935.
[17] Plotkin K J, Robertson J E. Prediction of space shuttle fluctuating pressure environment, including rocket plume effects, NASA-CR-124347[R]. WA, US: NASA, 1973.

第38卷
第5期
2017 年5月兵工学报ACTA
ARMAMENTARIIVol.38No.5May2017

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