Infrared signature of aircraft in supersonic flow

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

Research output: Contribution to conferencePaper

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 languageEnglish
Publication statusPublished - 2014 Jan 1
Event15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014 - Honolulu, United States
Duration: 2014 Feb 242014 Feb 28

Other

Other15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014
CountryUnited States
CityHonolulu
Period14/2/2414/2/28

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

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  • Cite this

    Kim, T., Cha, J., Bae, J. Y., Jung, D., & Cho, H. H. (2014). Infrared signature of aircraft in supersonic flow. Paper presented at 15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014, Honolulu, United States.