Heat transfer near injection hole by shock and boundary layer interaction in the supersonic flow field

Namkyu Lee, Jiwoon Song, Ji Yeul Bae, Yoon Goo Kang, Heecheol Ham, Ju Chan Bae, Hyung Hee Cho

Research output: Contribution to conferencePaperpeer-review


The flow structure and heat transfer coefficient are investigated using both experimental and numerical methods in the supersonic flowfield with transverse jet injection. The geometry of this research is an expansion nozzle with injection hole. The diameter of injection jet hole is 8.8 mm. The supersonic flow facility used in this research is the intermittent supersonic blow down tunnel. The expansion ratio of nozzle (A/A∗) has 4.23 at the outlet and 3.56 at the injection location. Selected jet-to-freestream momentum flux ratio is J = 0.5, 1.0 and 1.3 to verify the variation related to the momentum ratio near J = 1.0 which is common momentum ratio for secondary injection system. Flow structure with shock interaction at the surface is visualized by oil-lampblack and numerical simulation. Heat transfer on the surface is measured by IR thermography using transient method. Results show that the first separation point moves to the adverse direction of flow with increasing jet-tofreestream momentum ratio. Also, the peak value of heat transfer increases and moves farther from jet location due to penetration of transverse jet. These results will serve as fundamental database for thermal design of transverse jet.

Original languageEnglish
Publication statusPublished - 2014
Event15th International Heat Transfer Conference, IHTC 2014 - Kyoto, Japan
Duration: 2014 Aug 102014 Aug 15


Other15th International Heat Transfer Conference, IHTC 2014

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering
  • Condensed Matter Physics


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