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Volume 4 Issue 5
Sep.  2019
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Article Navigation >  PHYSICS OF GASES  > 2019  >  4(5): 25-31
YAO Xuan-yu, WANG Chun, YU Jiang, YUAN Chao-kai, JIANG Zong-lin, SITU Ming. High-Mach-Number Scramjet Engine Tests in JF12 Shock Tunnel[J]. PHYSICS OF GASES, 2019, 4(5): 25-31. doi: 10.19527/j.cnki.2096-1642.0788
Citation: YAO Xuan-yu, WANG Chun, YU Jiang, YUAN Chao-kai, JIANG Zong-lin, SITU Ming. High-Mach-Number Scramjet Engine Tests in JF12 Shock Tunnel[J]. PHYSICS OF GASES, 2019, 4(5): 25-31. doi: 10.19527/j.cnki.2096-1642.0788
shu

High-Mach-Number Scramjet Engine Tests in JF12 Shock Tunnel

doi: 10.19527/j.cnki.2096-1642.0788
  • 1.

    Aero Engine Academy of China, Beijing 101304, China

  • 2.

    SKL of High-Temperature Gasdynamics, Institute of Mechanics, CAS, Beijing 100190, China

  • 3.

    Beijing Power Machinery Research Institute, Beijing 100074, China

  • Received Date: 08 Jul 2019
  • Revised Date: 17 Jul 2019
  • Published: 20 Sep 2019
    Abstract
  • A schematic configuration of dual-step supersonic combustor was proposed to overcome the high gasdynamic drag of scramjet engine in high-Mach-number flight (Ma ≥ 7). Numerical simulations were conducted to evaluate the coupled mixing and combustion features of fuel jet and dual-step flowfield. A scramjet model with dual-step was designed and tested in the JF12 Shock Tunnel, which can provide the pure air medium for simulating high-Mach-number scramjet tests. During the 100 ms test duration of JF12 Shock Tunnel, successful ignition and stable combustion of hydrogen-fueled scramjet models were realized in both simulation conditions of Ma=7.0 and Ma=9.5 and the experimental results were compared. In the simulation condition of Mach 7, three-dimensional inlet was used and the entrance Mach number of supersonic chamber was about Mac=2.5. The wall pressure distributions showed that the combustion took place in the upstream of expansion section of duct. In the simulation condition of Mach 9.5, two-dimensional inlet was used and the entrance Mach number of supersonic chamber was about Mac=3.5. The combustion took place near the exit of inner duct of scramjet model.

     

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