Experimental Study of Supersonic Boundary Layer Transition Induced by Cylindrical Roughness Elements

被引：0
|
作者：
Jin L. [1 ]
Yi S. [1 ]
Huo J. [1 ]
Liu X. [1 ]
Niu H. [1 ]
机构：
[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
来源：
Shanghai Jiaotong Daxue Xuebao/Journal of Shanghai Jiaotong University | 2021年 / 55卷 / 08期
关键词：
Fractal dimension; Hairpin vortex; Nano-tracer-based planar laser scattering (NPLS); Roughness elements;
D O I：
10.16183/j.cnki.jsjtu.2020.221
中图分类号：
学科分类号：
摘要：
The boundary layer transition process induced by different heights and quantities of the cylindrical roughness elements at Mach 3.0 is investigated experimentally by using the nano-tracer-based planar laser scattering (NPLS) technique. Fine structures of the boundary layers of both streamwise and spanwise induced by the cylindrical roughness elements in the supersonic flow are obtained, and the development of the boundary layer in the roughness element wakes is observed. The boundary layer after reattachment will keep the laminar state within a certain distance, meanwhile hairpin vortexes can be observed clearly during the development of the boundary layer. The fractal theory is used to quantitatively analyze the NPLS images of the boundary layer. This method can achieve the positions of the boundary layer transition in several cases. The research results show that the interaction between multiple roughness elements can inhibit the boundary layer transition and the evolution of hairpin vortexes. However, when the roughness elements on both sides are higher than those in the middle, the interaction between roughness elements has no obvious inhibitory effects on the development of the boundary layer. © 2021, Shanghai Jiao Tong University Press. All right reserved.
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页码：942 / 948
页数：6
相关论文
共 17 条
  • [1] RESHOTKO E., Transition issues for atmospheric entry, Journal of Spacecraft and Rockets, 45, 2, pp. 161-164, (2008)
  • [2] BORG M P, SCHNEIDER S P., Effect of freestream noise on roughness-induced transition for the X-51A forebody, Journal of Spacecraft and Rockets, 45, 6, pp. 1106-1116, (2008)
  • [3] BERNARDINI M, PIROZZOLI S, ORLANDI P, Et al., Parameterization of boundary-layer transition induced by isolated roughness elements, AIAA Journal, 52, 10, pp. 2261-2269, (2014)
  • [4] BERRY S A, AUSLENDER A H, DILLEY A D, Et al., Hypersonic boundary-layer trip development for hyper-X, Journal of Spacecraft and Rockets, 38, 6, pp. 853-864, (2001)
  • [5] SCHNEIDER S P., Effects of roughness on hypersonic boundary-layer transition, Journal of Spacecraft and Rockets, 45, 2, pp. 193-209, (2008)
  • [6] CASPER K, WHEATON B, JOHNSON H, Et al., Effect of freestream noise on roughness-induced transition at Mach 6, 38th Fluid Dynamics Conference and Exhibit, pp. 1-25, (2008)
  • [7] ESTRUCH-SAMPER D, HILLIER R, VANSTONE L, Et al., Effect of isolated roughness element height on high-speed laminar-turbulent transition, Journal of Fluid Mechanics, 818, (2017)
  • [8] GANG Dundian, YI Shihe, ZHAO Yunfei, Experimental and numerical studies of supersonic flow over circular protuberances on a flat plate, Acta Physica Sinica, 64, 5, pp. 304-311, (2015)
  • [9] WHEATON B, SCHNEIDER S, BARTKOWICZ M, Et al., Roughness-induced instabilities at Mach 6: A combined numerical and experimental study, 41st AIAA Fluid Dynamics Conference and Exhibit, pp. 1-28, (2011)
  • [10] WHITEHEAD A H., Flow-field and drag characteristics of several boundary-layer tripping elements in hypersonic flow, (1969)
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