Infrared signature of aircraft in supersonic flow

Taehwan Kim; Jonghyun Cha; Ji Yeul Bae; Daeyoon Jung; Hyung Hee Cho

Infrared signature of aircraft in supersonic flow

Taehwan Kim, Jonghyun Cha, Ji Yeul Bae, Daeyoon Jung, Hyung Hee Cho

Department of Mechanical Engineering

Research output: Contribution to conference › Paper › peer-review

Abstract

The effects of viscous heating in supersonic flow on aircraft skin temperature are calculated by two commercial code, Fluent and RadthermIR. As a result, the skin temperature distribution which is affected by shock waves and aerodynamic heating on surface of aircraft is calculated. Second, the 8-12um maximum radiance at nose and wing leading edge is calculated by using the temperature data. This procedure can apply to other realistic combat aircraft and evaluate each IR stealth capability of aircraft.

Original language	English
Publication status	Published - 2014
Event	15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014 - Honolulu, United States Duration: 2014 Feb 24 → 2014 Feb 28

Other

Other	15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014
Country/Territory	United States
City	Honolulu
Period	14/2/24 → 14/2/28

All Science Journal Classification (ASJC) codes

Mechanical Engineering

Cite this

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title = "Infrared signature of aircraft in supersonic flow",

abstract = "The effects of viscous heating in supersonic flow on aircraft skin temperature are calculated by two commercial code, Fluent and RadthermIR. As a result, the skin temperature distribution which is affected by shock waves and aerodynamic heating on surface of aircraft is calculated. Second, the 8-12um maximum radiance at nose and wing leading edge is calculated by using the temperature data. This procedure can apply to other realistic combat aircraft and evaluate each IR stealth capability of aircraft.",

author = "Taehwan Kim and Jonghyun Cha and Bae, {Ji Yeul} and Daeyoon Jung and Cho, {Hyung Hee}",

year = "2014",

language = "English",

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T1 - Infrared signature of aircraft in supersonic flow

AU - Kim, Taehwan

AU - Cha, Jonghyun

AU - Bae, Ji Yeul

AU - Jung, Daeyoon

AU - Cho, Hyung Hee

PY - 2014

Y1 - 2014

N2 - The effects of viscous heating in supersonic flow on aircraft skin temperature are calculated by two commercial code, Fluent and RadthermIR. As a result, the skin temperature distribution which is affected by shock waves and aerodynamic heating on surface of aircraft is calculated. Second, the 8-12um maximum radiance at nose and wing leading edge is calculated by using the temperature data. This procedure can apply to other realistic combat aircraft and evaluate each IR stealth capability of aircraft.

AB - The effects of viscous heating in supersonic flow on aircraft skin temperature are calculated by two commercial code, Fluent and RadthermIR. As a result, the skin temperature distribution which is affected by shock waves and aerodynamic heating on surface of aircraft is calculated. Second, the 8-12um maximum radiance at nose and wing leading edge is calculated by using the temperature data. This procedure can apply to other realistic combat aircraft and evaluate each IR stealth capability of aircraft.

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M3 - Paper

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T2 - 15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014

Y2 - 24 February 2014 through 28 February 2014

ER -

Infrared signature of aircraft in supersonic flow

Abstract

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All Science Journal Classification (ASJC) codes

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