The Effects of Heat Shielding in Jet Engine Exhaust Systems on Aircraft Survivability

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The infrared signatures from hot engine parts pose major threats to military aircraft survivability. Reducing the skin temperature at the rear of the fuselage is key to reducing susceptibility to heat-seeking armaments. A heat shield placed between the nozzle wall and the outer casing of the engine can decrease the skin temperature at the rear of the fuselage. Therefore, numerical modeling of the fluid flow fields coupled with the radiative and conductive processes within the heat shield, nozzle, and casing were performed to determine the temperature distribution at the rear of the fuselage. The effect of the material properties and the dimensions of the heat shield were studied in order to determine their effects on the susceptibility of an aircraft.
Publisher
TAYLOR & FRANCIS INC
Issue Date
2014-07
Language
English
Article Type
Article
Keywords

FINITE-VOLUME METHOD; NOZZLE; FLOWS; ENCLOSURE; SPEEDS; MESHES; MODEL

Citation

NUMERICAL HEAT TRANSFER PART A-APPLICATIONS, v.66, no.1, pp.89 - 106

ISSN
1040-7782
DOI
10.1080/10407782.2013.869441
URI
http://hdl.handle.net/10203/188965
Appears in Collection
AE-Journal Papers(저널논문)
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