Effects of Geometry Parameters and Flow Parameters on Drag Coefficient of Upswept Afterbodies
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摘要: 利用N-S方程对9个上翘后体模型进行了气动力计算,主要研究后体几何参数和流动参数对上翘后体阻力系数的影响.研究结果表明, 后体的压差阻力系数分别随上翘角、收缩比的增加及迎角的减小而明显增加;后体摩擦阻力系数分别随后体的长细比的增加和雷诺数的减小而增加;后体越扁平,其压差阻力系数越大;在跨音速时,波阻系数也与上翘角有关,上翘角增加会导致波阻系数进一步加大.Abstract: The flows over upswept afterbodies were investigated by a numerical method based on 3D compressible N-S equations, in order to study effects of geometry parameters and flow parameters on drag coefficient of upswept afterbodies. The results showed that the pressure drag coefficient increases rapidly with increasing upswept angle and contraction ratio respectively, and with decreasing forebody incidence. The friction drag coefficient increases with increasing afterbody fineness ratio and decreasing Reynolds Number. The more the afterbody flatness, the more the pressure drag. The wave drag coefficient also increases with increasing upswept angle at transonic speed.
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Key words:
- separated flow /
- vortex /
- upswept afterbody
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[1] Wortman A. Reduction of fuselage form drag by vortex flows[J]. Journal of Aircraft,1999,36(3) [2] Epstein R J,Carbonaro M C,Caudron F. An experimental investigation of the flow field about an upswept afterbody. AIAA-94-1840-CP,1994 [3] Huang Y, Ghia U,Osswald G A, et al. Analysis and numerical simulation of 3-D flow past axisymmetric afterbody using Navier-Stokes equations. AIAA-93-0683,1993 [4] Kolesar C E, May F W. An aftbody drag prediction technique for military airlifters. AIAA-83-1787, 1983 [5] 孔繁美,华 俊,冯亚南,等.大上翘角机身后体流动机理研究. 空气动力学学报,2002,20(3):326~331 Kong Fanmei, Hua Jun, Feng Ya'nan, et al. Investigation of the flow mechanism on the afterbody with larger upswept angle[J]. Acta Aerodynamica Sinica,2002,20(3):326~331(in Chinese) -
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