Internal Flow Field Evolution Characteristics for Inlet Cover Separation of High Speed Inlet

被引：0
|
作者：
Zhao X.-Y. [1 ]
Wang Y. [1 ]
Fan X.-Q. [1 ]
Xu S.-C. [1 ]
机构：
[1] Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 05期
关键词：
Backward facing step; Inlet cover; Internal flow field; Overset method; Swept shock wave;
D O I：
10.13675/j.cnki.tjjs.190715
中图分类号：
学科分类号：
摘要：
To explore internal flow field on the inlet cover separation process, based on overset method to solve N-S equation, the evolution process of internal flow field and characteristic flow field structure were analyzed in detail during inlet cover separation. Numerical simulations show that a V- swept shock wave is formed at the front of the inlet cover, and a backward facing step that induces a pair of streamwise vortexes with the opposite vectors is formed at the rear of inlet cover when the inlet is blocked. On the separation process, the V-swept shock wave and the backward facing step both affect the internal flow. The mass flow rate at throat reaches its peak at intermediate moment then drops to a stable value. If the flow is quasi-steady and no large separation zone exists in the inner inlet during the separation process, inlet starts when the V-swept shock wave meets the lip line, and the motion of inlet cover no longer affects the internal flow field afterwards. The assumed constant acceleration rotation was consistent with the real rotation, and a more accurate motion simulation suggests the cubic angular velocity function. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：970 / 979
页数：9
相关论文
共 29 条
  • [21] Kim S E, Choudhury D, Patel B, Computations of Complex Turbulent Flows Using the Commercial Code Fluent, (1999)
  • [22] Ogawa H, Grainger A, Boyce R R., Inlet Starting of High-Contraction Axisymmetric Scramjets, Journal of Propulsion and Power, 26, 6, pp. 1247-1258, (2010)
  • [23] 4
  • [24] Heim E R., CFD Wing/Pylon/Finned Store Mutual Interference Wind Tunnel Experiment, (1991)
  • [25] (2014)
  • [26] (2017)
  • [27] Loth E, Kailasanath K, Lohner R., Supersonic Flow over an Axisymmetric Backward-Facing Step, Journal of Spacecraft and Rockets, 29, 3, pp. 352-359, (1992)
  • [28] Guo G M, Liu H, Zhang B., Numerical Study of Active Flow Control over a Hypersonic Backward-Facing Step Using Supersonic Jet in Near Space, Acta Astronautica, 132, pp. 256-267, (2017)
  • [29] Alvi F S, Settles G S., Physical Model of the Swept Shock Wave/Boundary-Layer Interaction Flowfield, AIAA Journal, 30, 9, pp. 2252-2258, (1992)
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