Effects of Inlet Flow Angle Distortion on Scramjet Nozzle

被引：0
作者：
Chen Y.-L. [1 ]
Yu K.-K. [1 ]
Xu J.-L. [1 ]
机构：
[1] College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Yu, Kai-Kai | 1600年 / Journal of Propulsion Technology卷 / 42期
关键词：
Aerodynamic performance; Flow angle distortion; Mach number distortion; Numerical simulation; Scramjet; Single expansion ramp nozzle;
D O I：
10.13675/j.cnki.tjjs.200195
中图分类号：
学科分类号：
摘要：
In order to explore the effects of the flow angle distortion on the aerodynamic performance of the Scramjet nozzle, the numerical simulation study of the nozzle under single flow angle distortion and coupled distortion inlet conditions was conducted. Firstly, the numerical simulation method applied in this study was introduced briefly; the accuracy of which was validated by the experiment and the grid resolution study was also conducted for obtaining an accurate numerical results. Secondly, the flow condition on the outlet of the Scramjet combustor was used to study the actual flow angle distortion on the aerodynamic performance of Scramjet nozzle. On this basis, the influence of the coupling between the flow angle distortion and the Mach number distortion on the aerodynamic performance of nozzle was further studied. From the numerical results, the influence of flow angle distortion on the thrust is still small, and the increment of thrust coefficient is only 0.37%. The lift still increases significantly by 51.84%, and the pitching moment increases by 12.11%. Further, it is found that the effects of flow angle distortion and Mach number distortion on the aerodynamic performance of nozzle are independent. Therefore, it is necessary to consider the influence of flow angle distortion in the design of the Scramjet nozzle. In addition, the variation of the lift and pitching moment by flow angle distortion should be paid attention since the lift affects the trim of the hypersonic vehicle. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：2694 / 2702
页数：8
相关论文
共 18 条
  • [1] Serre L, Falempin F., Promethee-The French Military Hypersonic Propulsion Program
  • [2] Steelant J., Achievements Obtained for Sustained Hypersonic Flight Within the LAPCAT Project
  • [3] Kazmar R R., Airbreathing Hypersonic Propulsion at Pratt & Whitney-Overview
  • [4] Edwards C L Q, Small W, Weidner J, Et al., Studies of Scramjet/Airframe Integration Techniques for Hypersonic Aircraft
  • [5] Yu Y, Xu J, Wang M., The Separation Pattern Transition Phenomena and Its Effects on the SERN Performance
  • [6] Meiss J H, Meinkey M, Schroderz W., Numerical Investigation to Enhance the Thrust Vector of a Scramjet Nozzle
  • [7] Baucco A R, Shanley K T, Bevis D., CFD Validation Study for Internal Performance of Advanced SERN Configurations
  • [8] TANG Lan, XU Jing-lei, MO Jian-wei, Et al., Reverse Design and Experiment Validation of Single Expansion Ramp Nozzle Based on Given Wall Pressure Distribution, Journal of Propulsion Technology, 37, 12, pp. 2226-2232, (2016)
  • [9] Ebrahimi H, Lankford D., Numerical Study of Phenomena Affecting the Prediction of Scramjet Combustor and Nozzle Performance
  • [10] Schindel L., Effect of Nonuniform Nozzle Flow on Scramjet Performance, Journal of Propulsion and Power, 15, 2, pp. 363-364, (1999)
12