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增升装置微型涡流发生器数值模拟方法研究 被引量:14

Investigation of Numerical Simulation Technique for Micro Vortex Generators Applied to High Lift System
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摘要 针对数值模拟带微型涡流发生器(VG)的增升装置绕流过程中出现的典型问题,研究相应解决途径。引入面搭接网格技术,避免传统结构网格方法造成的网格数量过大问题;在微型涡流发生器网格上采用特殊边界条件处理以分别对应有/无涡流发生器的状态,排除网格变动对计算结果造成的干扰;研发出了面搭接网格生成技术与特殊边界处理方法结合的求解加装微型涡流发生器的增升装置流动数值模拟方法。研究结果表明:该方法在处理增升装置这类复杂外形、复杂流动问题以及加装涡流发生器的流动控制问题时,具有良好的数值计算精度,能够满足研究需要,为开展涡流发生器精细设计和参数优化的数值模拟研究提供了可靠的技术途径。 To help carry out the numerical analysis of micro vortex generator(VG)used to control the flow separation of a high lift system,several crucial issues that occur during numerical simulation are solved in this paper.First,in order to avoid excessive grid number caused by the conventional point-to-point gird method,a patched grid technique is adopted.Second,a special boundary condition definition method is used to correspond respectively to the cases of the fitting and non-fitting of micro vortex generator,which will eliminate the disturbance caused by grid change.The combination of such two methods generates a new approach for the numerical analysis of a high lift system with micro vortex generator on it.The wind tunnel data prove that this approach achieves good numerical accuracy and can meet the needs of related research.It offers a reliable way during the numerical research of micro vortex generator design and parameter optimization.
出处 《航空学报》 EI CAS CSCD 北大核心 2012年第1期11-21,共11页 Acta Aeronautica et Astronautica Sinica
关键词 增升装置 流动分离 流动控制 微型涡流发生器 数值模拟 面搭接 湍流模型 high lift system flow separation flow control micro vortex generator numerical simulation patched grid turbulence model
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参考文献18

  • 1Meredit H P. Viscous phenomena affecting high lift sys- tems and suggestions for future CFD development. AGARD CP-515, 1993.
  • 2Gamer P L, Meredith P T, Stoner R C. Areas for future CFD development as illustrated by transport aircraft appli cations. AIAA-1991 1527, 1991.
  • 3Lin J C, Robinson S K. Separation control on high-lift air- foils via micro-vortex generators. AIAA-1994-46653, 1994.
  • 4Bohannon K S. Passive flow control on civil aircraft flaps using sub-boundary layer vortex generators in the AWlA- TOR programme. AIAA 2006-2858, 2006.
  • 5Brunet V, Francois C. Experimental and numerical inves tigations of vortex generators effects. AIAA-2006-3027, 2006.
  • 6Meunier M, Brunet V. High lift devices performance en- hancement using mechanical and air-jet vortex generators. AIAA-2008 36836, 2008.
  • 7黄静波,肖志祥,符松,张淼.超临界机翼表面涡流发生器影响研究[J].中国科学:技术科学,2010,40(8):867-878. 被引量:8
  • 8刘刚,刘伟,牟斌,肖中云.涡流发生器数值计算方法研究[J].空气动力学学报,2007,25(2):241-244. 被引量:38
  • 9von Stillfield F, Wallin S. Application of a statistical vor- tex generator model approach on the short-chord flap of a three-element airfoil . GRDI-2000-25205, 2000.
  • 10Godard G, Stanislas M. Control of a decelerating boundary layer. Part 1 :Optimization of passive vortex generator. Aer- ospace Science and Technology, 2006, 101 181-191.

二级参考文献34

  • 1倪亚琴.涡流发生器研制及其对边界层的影响研究[J].空气动力学学报,1995,13(1):110-116. 被引量:32
  • 2张进,张彬乾,阎文成,段卓毅,陈迎春,焦予秦,于新.微型涡流发生器控制超临界翼型边界层分离实验研究[J].实验流体力学,2005,19(3):58-60. 被引量:25
  • 3刘刚,刘伟,牟斌,肖中云.涡流发生器数值计算方法研究[J].空气动力学学报,2007,25(2):241-244. 被引量:38
  • 4Takallu M A. Reynolds-Averaged Navier-Stokes Simulation of Two Partial-Span Flap Wing Experiments. AIAA-1998-0701.
  • 5Mathias D L. Navier-Stokes Analysis of the Flow about a Flap Edge. AIAA-1995-0185.
  • 6Bohbot J, Grondin G. A Parallel Multigrid Conservative Patched/Sliding Mesh Algorithm for Turbulent Flow Computation of 3D Complex Aircraft Configurations. AIAA-2001-1006.
  • 7Robert W Waiters, James L Tomas. Aspects and Application of Patched Grid Calculations. AIAA-1986-1063.
  • 8James L Thumas, Robert W Waiters, Taekyu Reu. A Patched-Grid Algorithm for Towards the FIA-18 Aircraft Complex Configurations Directed. AIAA-1989-01.
  • 9HaiXin Chen, Song Fu. Navier-Stokes Simulations for Transport Aircraft Wing/Body High-Lift Configurations. Journal of Aircraft, 2003, 40(5): 883 -890.
  • 10Baker MD, Mathias DL, Roth KR, et al. Numerical investigation of slat and compressibility effects for a high-lift wing. AIAA Paper 99-0538, 1999.

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