|Table of Contents|

Performance calculation of two-dimensional supersonic inlet diffuser(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2017年06期
Page:
54-60
Research Field:
研究与设计
Publishing date:

Info

Title:
Performance calculation of two-dimensional supersonic inlet diffuser
Author(s):
WANG Kun1; 2;  XIE Lürong1; 2;  LIU Yu1; 2
1.College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China; 2.Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing 210016, China
Keywords:
supersonic inlet;  inlet diffuser;  law of centerline variation;  expansion ratio;  centerline offset
PACS:
V431-34
DOI:
-
Abstract:
The influences of the law of centerline variation, expansion ratio and centerline offset of two-dimensional supersonic inlet diffuser on aerodynamic performance and flow characteristics under inlet design condition are studied. The numerical results indicate that the inlet with diffuser rapid turning at its exit has maximum total pressure recovery coefficient and inlet with diffuser rapid turning at the entrance has minimum total pressure recovery coefficient; as the expansion ratio increases from 1.40 to 1.80, inlet total pressure recovery coefficient and backpressure-resistance ability decrease, and the exit Mach number increase; the effect of expansion ratio and length on inlet exit parameter has a strong coupling relationship. As offset ratio increases, the inlet total pressure recovery coefficient increases at the beginning, but as the offset ratio increases to more than 0.80, the inlet total pressure recovery coefficient declines and the exit Mach number increases. General speaking, the variation of offset ratio has little effect on backpressure-resistance ability of the inlet.

References:

[1] SAJBEN M, BOGAR T J, KROUTIL J C. Expermental study of flows in a two-dimensional inlet model [J]. Journal of propulsion and power, 1985, 1(2): 109-117.
[2] SAJBEN M, BOGAR T J, KROUTIL J C. Experimental investigation of terminal shock sensors for mixed-compression inlets [J]. Journal of propulsion and power, 1992, 8(1): 168-174.
[3] BOGAR T J, SAJBEN M, KROUTIL J C. Characteristics frequencies of transonic diffuser flow oscillations [J]. AIAA journal, 1983, 21(9): 1232-1240.
[4] IKUI T, MATSUO K, MOCHIZUKI H, et al. Pseudo-shock waves in a divergent channel [J]. Bull JSME,1980, 23(175): 20-25.
[5] IKUI T, MATSUO K, SASAGUCHI K. Modified diffusion model of pseudo-shock waves considering upstream boundary layer [J]. Bull JSME, 1981, 24(197): 1920-1927.
[6] HSIEH T, WARDLAW A B, COAKLEY T. Ramjet diffuser flowfield response to large-amplitude combustor pressure oscillations [J]. Journal of propulsion and power, 1987, 3(5): 472-477.
[7]HSIEH T, BOGAR T J, COAKLEY T. Numerical simulation and comparison with experiment for self-excited oscillations in a diffuser flow [J]. AIAA journal, 1987, 25(7): 936-943.
[8] KAWATSU K, KOIKE S, KUMASAKA T, et al. Pseudo-shock wave produced by backpressure in straight and diverging rectangular ducts [C]//Proceedings of AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. [S.l.]: AIAA, 2005: 2005-3285.
[9] WEISS A, GRZONA A, OLIVIER H. Behavior of shock trains in a diverging duct [J]. Exp fluids, 2010, 49: 355-365.
[10] WEISS A, OLIVIER H. Behavior of a shock train under the influence of boundary-layer suction by a normal slot [J]. Exp fluids, 2012, 52: 273-287.
[11] HYOUNG J L, BOK J L. Flow characteristics of small-sized supersonic inlets [J]. Journal of propulsion and power, 2011, 27(2): 306-318.
[12] 谭慧俊,郭荣伟. 二维弯曲等截面管道中的激波串特性研究[J].航空动力学报,2006,27(6):1039-1045.
[13] TAN Huijun, SUN Shu. Preliminary study of shock train in a curved variable-section diffuser [J]. Journal of propulsion and power, 2008, 24(2): 245-252.
[14] 安彬,范晓樯,李腾骥,等. 等截面S弯隔离段流场特性研究[R].第十七届中国空气动力学物理气体动力学学术交流会, 2015.
[15] GUO Shanguang, WANG Zhenguo, ZHAO Yuxin. Contour design of super / hypersonic dual-Inflection nozzle [J]. Journal of aerospace power, 2012, 27( 12): 2742 -2748.
[16] 郭善广,王振国,赵玉新. 超声速转弯流道内的迟滞现象[J]. 国防科技大学学报, 2014, 36(4): 10-14.
[17] LEE C, BOEDICKER C. Subsonic diffuser design and performance for advanced fighter aircraft: AIAA 85-3073 [R]. USA: AIAA, 1985.
[18] REINARTZ B U, HERRMAN C D, BALLMANN J. Aerodynamic performance analysis of a hypersonic inlet isolator using computation and experiment [J]. Journal of propulsion and power, 2003, 19(5): 868-875.

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