Hyoung Jin Lee/In-Seuck Jeung/Seoung-Lyoung Kim/Insun Kim
International Journal of Aeronautical and Space Sicences, vol. 11, no. 3, pp.193-200, 2010

Abstract : 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.

Keyword : Protuberance, Hypersonic, Heat flux, Coaxial-thermocouple, Temperature--sensitive-paint