• Title/Summary/Keyword: Temperature--sensitive-paint

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Comparative Study of the Steady State and Transient TSP Techniques in the Heat Transfer Measurement by an Inclined Impingement Jet (경사 충돌 제트 열전달 실험에서 정상 상태와 천이 TSP 기법의 비교 연구)

  • Jo, Yong-Hwa;Nho, Young-Cheol;Lee, Yong-Jin;Kwak, Jae-Su
    • The KSFM Journal of Fluid Machinery
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    • v.15 no.1
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    • pp.5-12
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    • 2012
  • In this paper, the heat transfer coefficient measurement techniques using TSP(temperature sensitive paint) were introduced and the results of a comparative study on the heat transfer coefficient measurement by steady state and transient TSP techniques were discussed. The distributions of heat transfer coefficient by a single $60^{\circ}$ inclined impingement jet on a flat surface were measured by both techniques. Tested Reynolds number based on the jet diameter (d) was 30,000 and the distance between jet exit and target plate (L) was fixed at 10d. Results showed that the measured Nusselt number by both techniques indicated significant difference except near the center of impingement jet. Also, the heat transfer coefficients measured by the transient TSP technique were affected by the reference temperature of the jet. Based on the measured data, characteristics of both TSP techniques were analyzed and suggestions for applying them were also given.

A Study on Dynamic Characteristics Analysis of Hybrid Wind Power Blades according to Material Properties Method (물성치 적용 기법에 따른 하이브리드 풍력 블레이드 동적특성 해석에 관한 연구)

  • Kang, Byong-Yun;Han, Jeong-Young;Hong, Cheol-Hyun;Moon, Byong-Young
    • The KSFM Journal of Fluid Machinery
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    • v.15 no.2
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    • pp.5-11
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    • 2012
  • In this paper, the heat transfer coefficient measurement techniques using TSP(temperature sensitive paint) were introduced and the results of a comparative study on the heat transfer coefficient measurement by steady state and transient TSP techniques were discussed. The distributions of heat transfer coefficient by a single $60^{\circ}$ inclined impingement jet on a flat surface were measured by both techniques. Tested Reynolds number based on the jet diameter (d) was 30,000 and the distance between jet exit and target plate (L) was fixed at 10d. Results showed that the measured Nusselt number by both techniques indicated significant difference except near the center of impingement jet. Also, the heat transfer coefficients measured by the transient TSP technique were affected by the reference temperature of the jet. Based on the measured data, characteristics of both TSP techniques were analyzed and suggestions for applying them were also given.

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

  • Lee, Hyoung-Jin;Lee, Bok-Jin;Jeung, In-Seuck;Kim, Seoung-Lyoung;Kim, In-Sun
    • International Journal of Aeronautical and Space Sciences
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    • v.11 no.3
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    • pp.193-200
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    • 2010
  • 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.

Aerodynamic Measurement over a Protuberance in Hypersonic Flows Using Coaxial Thermocouple and TSP (동축열전대 및 TSP를 이용한 극초음속 유동 내 돌출물 주위 공력가열 계측)

  • Lee, Hyoung-Jin;Lee, Bok-Jik;Jeung, In-Seuck;Kim, Seong-Lyong;Kim, In-Sun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.10
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    • pp.967-974
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    • 2009
  • Experiments were conducted to measure the heat flux and temperature over a protuberance, using an impulse hypersonic shock tunnel-coaxial thermocouples and a blowdown hypersonic wind tunnel-temperature sensitive paints(TSP). Experimental data were compared with the heat flux data using a blowdown hypersonic wind tunnel-heat flux gauges and it was confirmed data sets agreed well. The measured heat flux is large when the height of the protuberance is large. Also, the heat flux measurements at the upper positions are larger than at the lower positions. For high protuberances, a severe jump in the heat flux is observed, from about 0.6~0.7 of the height of the protuberances. However, when the protuberance is sufficiently short, a rise in the heat flux is rarely observed as the protuberance is submerged totally under the separation region.