Parametric Design and Flow Analysis of Dual-Lateral Diverterless Supersonic Inlet

被引：0
作者：
Qiao W.-Y. [1 ]
Jin Y.-N. [1 ]
Ren Z. [1 ]
Yu A.-Y. [2 ]
Si R. [3 ]
机构：
[1] Research Center of Combustion Aerodynamics, Southwest University of Science and Technology, Mianyang
[2] Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang
[3] Chengdu Aircraft Design and Research Institute, Chengdu
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 03期
关键词：
Distortion; Inlet; Liutex; S-bend tube; Streamwise vortex;
D O I：
10.13675/j.cnki.tjjs.210831
中图分类号：
学科分类号：
摘要：
In view of the large distortion caused by streamwise vortex in the S-bend of dual-lateral diverter-less supersonic inlet，a parametric design method was proposed，and an inlet configuration was designed based on the typical aircraft forebody. The flow mechanism inside the S-bend was analyzed by using Liutex vortex identification method，and the design method was explored to improve the flow field quality of inlet. The results show that the Liutex vortex identification method can effectively identify the size and intensity of streamwise vortex in the flowfield of the S-bend. In order to suppress the generation and development of streamwise vortex and reduce the distortion of the outlet，the configuration on the upper lip side at the inlet entrance should have a smaller curvature，and on the lower lip side curvature should be increased. The end of the flow channel should be twisted to push the streamwise vortex into the centre of the outlet. The study can effectively suppress the distortion of the outlet，and explore a new design method to control the streamwise vortex inside the flow channel. © 2023 Journal of Propulsion Technology. All rights reserved.
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共 24 条
  • [1] Gridley M C, Walker Steven H., Inlet and Nozzle Technology for 21st Century Fighter Aircraft
  • [2] Gridley M C，, Cahill M J., ACIS Air Induction System Trade Study, (2000)
  • [3] Kim S D., Aerodynamic Design of a Supersonic Inlet with a Parametric Bump［J］, Journal of 粤ircraft, 46, 1, pp. 198-202, (2009)
  • [4] Kim S D, Song D J，, Lim S., A Numerical Analysis on Three-Dimensional Flow Field in a Supersonic Bump Inlet ［R］
  • [5] (2004)
  • [6] 26, 3, pp. 286-289, (2005)
  • [7] 20, 5, pp. 740-745, (2005)
  • [8] 25, 3, pp. 336-339, (2007)
  • [9] 39, 4, pp. 449-452, (2007)
  • [10] 30, 9, pp. 1597-1604, (2009)
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