Radiative Heat Transfer from a Shock Layer Generated around a Projectile Launched in a Ballistic Range

  • Kimiya Komurasaki
  • Jiro Kasahara
  • Shujiro Yano
  • Toshi Fujiwara
Conference paper


Radiative heat transfer from a strong shock layer over a hypersonic flight vehicle is experimentally investigated using a ballistic range facility. A plastic projectile of 1.2 cm diameter is accelerated in this facility up to 5.3 km/s (M =15), and the radiation spectra and global power emission from the launched projectile are measured. As a result, the radiant intensity from the shock layer became approximately 300 W/m2sr, and the carbon radiation spectra were observed along with the air spectra. In order to take account of model-dimension effects of the projectile, which is two orders of magnitude smaller than the actual size of the vehicles, a scaling law has been developed by analytical and numerical considerations. The computed results are compared with the measured ones, and the validity of the calculation model including the wall condition is discussed.

Key words

Radiative heat transfer Shock layer structure Ballistic range Hypersonic flow 



shock layer thickness or shock stand-off distance, m


Mach number


total mole density, mole/m3


pressure, Pa


nose radius of the blunt body, m

T, Tv

translational and vibrational temperature, K


geometric average temperature, K


local flow velocity, m/sec


thermal boundary thickness, m

λV, λR

vibrational-relaxation distance and reaction distance, m


vibrational-relaxation time and reaction time, sec


density, kg/m3


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Copyright information

© Springer-Verlag Berlin Heidelberg 1995

Authors and Affiliations

  • Kimiya Komurasaki
    • 1
  • Jiro Kasahara
    • 1
  • Shujiro Yano
    • 1
  • Toshi Fujiwara
    • 1
  1. 1.Department of Aeronautical EngineeringNagoya UniversityNagoya 464-01Japan

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