To deal with the low total pressure recovery rate and the high distortion level of serpentine inlets designed with the traditional method, a novel design concept of serpentine inlets based on surface vortex controlled global secondary flow reconstruction is presented in this paper. The simulation validation for the concept shows that:1) the vortex-controlled model successfully alleviates the large separation occurring on the top surface of the baseline model, which is because the vortex induced by the vortex-controlled design rotates in a direction opposite to that of the baseline vortex responsible for the separation; 2) the vortex-controlled model reduces circumferential distortion (as calculated by the DC60 descriptor) by 76% while improving the total pressure recovery by 0.84%. These results demonstrate the feasibility of the vortex-controlled design concept for serpentine inlets.
XIE Wenzhong, GUO Rongwei
. Vortex-controlled Design Research for Serpentine Inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(10)
: 1806
-1814
.
DOI: CNKI:11-1929/V.20110426.1122.007
[1] Ray W. Designing for stealth in fighter aircraft. SAE Paper 965540, 1996.
[2] Mayer D W, Anderson B H, Johnson T A. 3D subsonic diffuser design and analysis. AIAA-1998-3418, 1998.
[3] 朱宇, 王霄. 短S形进气道流动特性数值模拟研究[J]. 飞机设计, 2004(4): 1-6. Zhu Yu, Wang Xiao. A numerical simulation investigation of flow characteristics for short-S inlet ducts[J]. Aircraft Design, 2004(4): 1-6. (in Chinese)
[4] Brear M J, Warfield Z, Mangus J F, et al. Flow separation within the engine inlet of an uninhabited combat air vehicle (UCAV)[J]. Journal of Fluids Engineering, 2004,126(2): 266-272.
[5] Rabe A. Serpentine inlet total pressure measurements//Virginia Tech and Technology in Blacksburg. 2001.
[6] Tormalm M. Design and analysis of compact UAV ducts. AIAA-2006-2828, 2006.
[7] Sun S, Guo R W. Serpentine inlet performance enhancement using vortex generator based flow control[J].Chinese Journal of Aeronautics, 2006, 19(1): 10-17.
[8] Xie W Z, Guo R W. A ventral diverterless high offset S-shaped inlet at transonic speeds[J]. Chinese Journal of Aeronautics, 2008, 21(3): 207-214.
[9] 谢文忠, 郭荣伟.腹下无隔道大偏距跨声速S弯进气道流场特性研究[J].航空学报, 2008,29(6): 1460-1466. Xie Wenzhong, Guo Rongwei. Flow field of ventral diverterless high offset S-shaped inlet at transonic speeds[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(6): 1460-1466. (in Chinese)
[10] 张航, 谭慧俊, 李湘萍. 类X-47狭缝式进气道的流动特征与工作性能[J].航空学报, 2009,30(12): 2243-2249. Zhang Hang, Tan Huijun, Li Xiangping. Flow structure and performance characteristics of X-47 like slot-shaped inlet[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(12): 2243-2249. (in Chinese)
[11] Amitay M, Parekh D, Pitt D, et al. Control of internal flow separation using synthetic jet actuators. AIAA-2000-903,2000.
[12] Hamstra J W, Miller D N, Truax P P, et al. Active inlet flow control technology demonstration//ICAS 2000 International Council of the Aeronautical Sciences Congress. 2000: 473-479.
[13] Zhou J, Tang H, Zhong S. Vortex roll-up criterion for synthetic jets[J]. AIAA Journal, 2009, 47(5): 1252-1262.
[14] Zhang P F, Wang J J, Feng L H. Review on the zero-net-mass-flux jet and the application in separation flow control[J]. Science in China Series E: Technological Sciences,2008, 51(9): 1315-1344.
[15] Harper D K. Boundary layer control and wall pressure fluctuations in a serpentine inlet. Virginia: Virginia Polytechnic Institute and State University, 2000.
[16] Reichert B, Wendt B. Improving diffusing S-duct performance by secondary flow control. AIAA-1994-365, 1994.
[17] Greitzer E M, Tan C S, Graf M B. Internal flow[M]. Cambridge: Cambridge University Press, 2004.
[18] Squire H B, Winter K G. The secondary flow in a cascade of airfoils in a non-uniform stream[J]. Journal of the Aeronautical Sciences, 1951,18: 271-277.
[19] Perry A E, Chong M S. A series expansion study of the Navier-Stokes equations with applications to three-dimensional separation patterns[J]. Journal of Fluid Mechanics, 1986, 173: 207-223.
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