Unstart Characteristics of High Speed Inlet at Low Mach Number and Influence Law of Mach Number

被引：0
|
作者：
He L.-H. [1 ,2 ]
Zhang Q.-F. [1 ]
Yue L.-J. [1 ]
Zhang X.-Y. [1 ,2 ]
Wang W.-X. [3 ]
Tan H.-J. [3 ]
机构：
[1] State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing
[2] College of Engineering Science, University of Chinese Academy of Sciences, Beijing
[3] College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 10期
关键词：
Aerodynamic force; High speed inlet; Low Mach number unstart; Self-start; Unsteady;
D O I：
10.13675/j.cnki.tjjs.200090
中图分类号：
学科分类号：
摘要：
In order to explore the oscillation characteristics of the inlet unstart induced by the low Mach number inflow, an unsteady simulation study of a specific integration of the forebody and the inlet was carried out. A comparison of the oscillation flow field and the aerodynamic force of the aircraft under different incoming Mach numbers were performed. The results show that a stable periodic oscillation appears when the inlet is unstart at the low Mach number. And the cycle length of the periodic oscillation increases with the increase of the incoming Mach number. Due to the throttling in the inlet throat, the oscillation flow field can be divided into two stages, which are the increasing and decreasing stages of the separation bubble in the throat. Meanwhile, the distribution trends of the mean and amplitude of the pressure along the tunnel both exhibit high at throat and low at both ends. And the increase of inflow Mach number will increase such trend. In the oscillation period, the variation trends of the lift coefficient CL and the drag coefficient CD are quite different, while the lift drag ratio curve is manifested as the trend of increasing with the throwing up of the separation bubble and decreasing with the swallowing of the separation bubble. CL and CD decrease with the increase of Mach number, but the amplitude of pulsation changes little, and the lift drag ratio is not sensitive to the change of Mach number. CL and CD both decrease with the increase of Mach number, but the amplitude of oscillation changes little. And the lift-drag ratio is not sensitive to the change of Mach number. In addition, in the process of self-starting, it is found that once the instantaneous flow in the throat is higher than that in the starting to a certain extent, the separation bubble at the throat can be swallowed completely. Because the swallowing process cannot be simulated by the steady simulation accurately, the self-starting Mach number obtained by the steady simulation is higher. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：2207 / 2217
页数：10
相关论文
共 24 条
  • [1] (2012)
  • [2] 12, pp. 25-32
  • [3] Curran E T, Murthy S N B., Scramjet Propulsion, (2001)
  • [4] Oswatitsch K, Der Wir-kungsgrad vos Stossdiffusoren. Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds, (1944)
  • [5] Newsome R W., Numerical Simulation of Near-Critical and Unsteady, Subcritical Inlet Flow, AIAA Journal, 22, 10, pp. 1375-1379, (1984)
  • [6] Lu P J, Jain L T., Numerical Investigation of Inlet Buzz Flow, Journal of Propulsion and Power, 14, 1, pp. 90-100, (1998)
  • [7] Trapier S, Duveau P, Deck S., Experimental Study of Supersonic Inlet Buzz, AIAA Journal, 44, 10, pp. 2354-2365, (2006)
  • [8] Trapier S, Deck S, Duveau P., Time Frequency Analysis and Detection of Supersonic Inlet Buzz, AIAA Journal, 45, 9, pp. 2273-2284, (2007)
  • [9] Trapier S, Deck S, Duveau P., Delayed Detached-Eddy Simulation and Analysis of Supersonic Inlet Buzz, AIAA Journal, 46, 1, pp. 118-131, (2008)
  • [10] Lee H J, Lee B J, Kim S D, Et al., Flow Characteristics of Small-Sized Supersonic Inlets, Journal of Propulsion and Power, 27, 2, pp. 306-318, (2011)
123