Shock Waves pp 891-896 | Cite as

Experimental studies on model scramjet in a Mach 6 high enthalpy free-jet wind tunnel

  • X. Y. Chang
  • L. H. Chen
  • H. B. Gu
  • G. Yu
Conference paper


A side-wall compression scramjet model with different combustor geometries has been tested in a propulsion tunnel that typically provides the testing flow with Mach number of 5.8, total temperature of 1800K, total pressure of 4.5MPa and mass flow rate of 4kg/s. This kerosene-fueled scramjet model consists of a side-wall compression inlet, a combustor and a thrust nozzle. A strut was used to increase the contraction ratio and to inject fuels, as well as a mixing enhancement device. Several wall cavities were also employed for flame-holding. In order to shorten the ignition delay time of the kerosene fuel, a little amount of hydrogen was used as a pilot flame. The pressure along the combustor has an evident raise after ignition occurred. Consequently thrust was observed during the fuel-on period. However, the thrust was still less than the drag of the scramjet model. For this reason, the drag variation produced by different strut and cavities was tested. Typical results showed that the cavities do not influence the drag so much, but the length of the strut does.


Mach Number Mass Flow Rate Drag Coefficient Ignition Delay Time Supersonic Combustion 
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Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • X. Y. Chang
    • 1
  • L. H. Chen
    • 1
  • H. B. Gu
    • 1
  • G. Yu
    • 1
  1. 1.Laboratory of High Temperature Gas Dynamics, Institute of MechanicsChinese Academy of SciencesBeijingChina

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