Numerical investigation of rectangular-to-circular isolator under asymmetric incoming flow

被引：0
|
作者：
Wang Y. [1 ]
Zhang K.-Y. [2 ]
机构：
[1] Sino-European Institute of Aviation Engineering, Civil Aviation University of China, Tianjin
[2] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Tuijin Jishu | / 12卷 / 2243-2250期
关键词：
Asymmetric incoming flow; Isolator; Numerical investigation; Rectangular-to-circular; Scramjet;
D O I：
10.13675/j.cnki.tjjs.2016.12.006
中图分类号：
学科分类号：
摘要：
The performance of Rectangular-to-Circular isolator based on super elliptical method affected by various factors such as back pressure, incoming Mach number and boundary layer thickness was investigated with numerical simulation under asymmetric incoming flow. The results show that the interaction of back pressure and boundary layer leads to the initial shock wave form gradually transforming into "λ" shock, and the increase of back pressure results in the decrease of isolator's performance, the sharp increase of low energy flow region, as well as the decrease of the asymmetric effect of flow field. Meanwhile the increase of incoming Mach number leads to the improvement of the withstand back pressure capability of isolator, while the effect of asymmetric flow field declined consequently, especially the total pressure recovery coefficient of outlet section decrease 7.2% while incoming Mach number of 2.5 compared with situation where Mach number is 2. The increase of boundary layer thickness contributes to deterioration of the flow separation in the isolator, which further results in the decline of the withstand back pressure capability of isolator, which is not conducive to the quality of the exit flow field of isolator. When the dimensionless thickness of boundary layer is 0.33, the total pressure recovery coefficient of outlet section under asymmetric incoming flow declines 13.7% than it is under uniform inflow. © 2016, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：2243 / 2250
页数：7
相关论文
共 16 条
  • [1] Pratt D.T., Heiser W.H., Isolator-Combustor Interaction in a Dual Mode Scramjet Engine
  • [2] Carroll B.F., Dutton J.C., Multiple Normal Shock Wave/Turbulent Boundary-Layer Interactions, Journal of Propulsion and Power, 8, 2, pp. 441-448, (1992)
  • [3] Neumann E.P., Lustwerk F., High-Efficiency Supersonic Diffusers, Journal of Aeronautical Sciences, 18, 6, pp. 369-374, (1951)
  • [4] Ikui T., Matsuo K., Nagai M., The Mechanism of Pseudo-Shock Waves, Bulletin of the Japan Society of Mechanical Engineering, 17, 108, pp. 731-739, (1974)
  • [5] Ikui T., Matsuo K., Sasaguchi K., Modified Diffusion Model of Pseudo-Shock Waves Considering Upstream Boundary Layers, Bulletin of the Japan Society of Mechanical Engineering, 24, 197, pp. 1920-1927, (1981)
  • [6] Matsuo K., Miyazato Y., Kim H.D., Shock Train and Pseudo-Shock Phenomena in Internal Gas Flows, Progress in Aerospace Sciences, 35, 1, pp. 33-100, (1999)
  • [7] Waltrup P.J., Billig F.S., Structure of Shock Waves in Cylindrical Ducts, AIAA Journal, 11, 10, pp. 1404-1408, (1973)
  • [8] Carroll B.F., Dutton J.C., Characteristics of Multiple Shock Wave/Turbulent Boundary-Layer Interactions in Rectangular Ducts, Journal of Propulsion and Power, 6, 2, pp. 186-193, (1990)
  • [9] Carroll B.F., Lopez-Fernandez P.A., Dutton J.C., Computations and Experiments for a Multiple Normal Shock/ Boundary-Layer Interaction, Journal of Propulsion and Power, 9, 3, pp. 405-411, (1993)
  • [10] Lin P., Rao G.V.R., O'Connor G.M., Numerical Analysis of Normal Shock Train in a Constant Area Isolator
12