International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Overview of Flow Diagnosis in a Shock Tunnel

  • Kim, Ikhyun (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Lee, Sungmin (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Park, Gisu (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Lee, Jong Kook (The 1st Research and Development Institute, Agency for Defense Development)
  • Received : 2017.06.12
  • Accepted : 2017.08.05
  • Published : 2017.09.30
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Abstract

In this work, an overview of flow diagnosis in a shock tunnel is made by means of using established techniques that are easy to setup, economical to arrange, and simple to measure. One flow condition was considered having Mach number of 6 at the nozzle-exit, regarded as freestream. Measured aerothermodynamic data such as shock wave speed, wall static and total pressures, surface heat flux, and shock stand-off distance ahead of test model showed good agreement with calculation. This study shows an overall procedure of flow diagnosis in a shock tunnel in a single manuscript. Outcomes are thought to be useful in the field of education and also in a preliminary stage of high-speed vehicle design and tests, that need to be performed within a short time with decent accuracy.

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References

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