Gi-su Park
Korea Advanced Institute of Science and Technology · Engineering
About the Lab
Professor Gi-su Park's research lab specializes in hypersonic flow physics, with a focus on experimental and computational investigations of high-speed aerodynamics, including near-wake flows, base flows, and shock-boundary layer interactions. The lab conducts fundamental studies on catalytic heat transfer, gas-surface interactions, and combustion phenomena in extreme environments, such as those encountered in planetary entry and re-entry. Key research directions include hypersonic vehicle thermal protection systems, nonequilibrium gas dynamics, and droplet breakup in high-speed flows. The lab employs advanced ground-based facilities such as shock tunnels, expansion tubes, and free-piston shock tunnels to simulate flight conditions at Mach 10 and beyond.
Research Overview
Research Output Trend
Figures are computed from collected data and may differ slightly.
Selected Papers
15The laminar near-wake flow behind a circular cylinder at hypersonic speeds has been examined experimentally and analytically. Surface pressure and heat flux measurements were obtained in a free-piston shock tunnel at a nominal Mach number of 10. The freestream unit Reynolds numbers were 3.02 x 10 5 /m and 11.7 x 10 5 /m at total specific enthalpies of 13.35 and 3.94 MJ/kg, respectively. The experimental data of surface pressure and heat flux showed good agreement with theory based on perfect gas
This paper presents experimental and theoretical results on catalytic phenomenon occurring in a test gas consisting of a mixture of 21% oxygen and 79% argon. The heat-transfer rates at the stagnation point of a blunt body are measured in a shock tube using a thin-film gauge. The surface of the test model was coated with silicon dioxide, copper oxide, or copper. The copper-coated model showed a heat-transfer-rate value 45% higher than that to a silicon-dioxide-coated model and 28% higher than tha
The paper presents a computational and an experimental investigation of base flow of a circular cylinder at hypersonic speeds. Effects of chemistry and wall temperature on the flow in the base region, at low to high enthalpies, are discussed. The experiments were conducted in a shock tunnel at a nominal Mach number of 10. Freestream Reynolds numbers based on cylinder diameter were and , respectively, and the total specific enthalpies were 13.35 and , respectively. The test gas was air. The surfa
Flowfield and flame-holding characteristics of ethylene jets were examined experimentally. Flow visualization and chemiluminescence images were obtained in a shock tunnel. Model configurations with and without a cowl or a cavity were tested for jet-to-freestream momentum flux ratios varying from 1.35 to 3.07. Flame-holding characteristics were studied using a cavity configuration with a cowl. Four flow conditions with the total temperature varying from 1610 to 2320 K were studied keeping the ove
Research Areas
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