The IR radiation characteristics of aeroengine are the important basis for IR stealth design and anti-stealth detection of
aircraft. With the development of IR imaging sensor technology, the importance of aircraft IR stealth increases. An effort
is presented to explore target IR radiation imaging simulation based on Reverse Monte Carlo Method (RMCM), which
combined with the commercial CFD software. Flow and IR radiation characteristics of an aeroengine exhaust system are
investigated, which developing a full size geometry model based on the actual parameters, using a flow-IR integration
structured mesh, obtaining the engine performance parameters as the inlet boundary conditions of mixer section, and
constructing a numerical simulation model of engine exhaust system of IR radiation characteristics based on RMCM.
With the above models, IR radiation characteristics of aeroengine exhaust system is given, and focuses on the typical
detecting band of IR spectral radiance imaging at azimuth 20°. The result shows that: (1) in small azimuth angle, the IR
radiation is mainly from the center cone of all hot parts; near the azimuth 15°, mixer has the biggest radiation
contribution, while center cone, turbine and flame stabilizer equivalent; (2) the main radiation components and space
distribution in different spectrum is different, CO2 at 4.18, 4.33 and 4.45 micron absorption and emission obviously, H2O
at 3.0 and 5.0 micron absorption and emission obviously.