Aerodynamic Heating Characteristics Over a Protuberance in Hypersonic Flows Using Fast Response Thermo Gauges

  • Lee, Hyoung-Jin (LIG Nex1 Co., Ltd., Korea School of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Lee, Bok-Jin (LIG Nex1 Co., Ltd., Korea School of Mechanical and Aerospace Engineering, Seoul National University) ;
  • Jeung, In-Seuck (Department of Aerospace Engineering and Institute Advanced Aerospace Technology, Seoul National University) ;
  • Kim, Seoung-Lyoung (Korea Aerospace Research Institute) ;
  • Kim, In-Sun (Korea Aerospace Research Institute)
  • 발행 : 2010.09.15


Through experimental investigations utilizing hypersonic shock tunnel-coaxial thermocouples as well as blow down hypersonic wind tunnel-temperature sensitive paints, the heat flux and the temperature over a protuberance were measured and analyzed. The experimental data were subsequently compared to heat flux data that was obtained by using blow down hypersonic wind tunnel and heat flux gauges. According to the comparison, both sets of data illustrated correlation with one another. The measured heat flux was large when the height of the protuberance was large. Experimental results show that heat flux measurements taken at higher locations were greater than those taken at lower locations. For high protuberances, a severe jump in the heat flux was observed, ranging in values within 0.6-0.7 of the height of the protuberances. However, when the protuberance was sufficiently short, a rise in the heat flux was rarely observed as the protuberance was totally submerged under the separation region.



연구 과제 주관 기관 : National Research Foundation of Korea (NRF)


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피인용 문헌

  1. Hypersonic Interference Heating on Flat Plate with Short Three-Dimensional Protuberances vol.52, pp.4, 2014,
  2. Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds vol.135, pp.12, 2013,