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.
|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||15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2014|
|Period||14/2/24 → 14/2/28|
All Science Journal Classification (ASJC) codes
- Mechanical Engineering