Turbine Engine Infrared Signature Program.
Final rept. 3 Jul 72-31 Oct 75,
PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
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This report describes the results of a forty-month program carried out as part of Air Force Contract F33615-72-C-1840 to formulate and validate a computer model to provide a realistic simulation of engine infrared radiation in an aircraft environment. The aerodynamic model provides an accurate definition of plume flowfield properties by employing solutions which define the shock systems inclusive of the Mach disc and the viscous interaction between different engine gas streams and the external flow. Using the flowfield properties as defined by the aerodynamic model, the plume infrared emissions are evaluated by a plume model which employs a long characteristics approach and a modified Curtis-Godson scaling approximation. The internal flow model provides an accurate definition of the exhaust system internal flowfield properties and wall temperatures. Using these properties, the infrared emissions due to the hot parts of the exhaust system are calculated using a hot parts computer model which accounts for direct emissions and inter-reflections, variation in surface properties, and absorption by intervening gas streams. The total system is coupled with an atmospheric attenuation model to form the Turbine Engine Infrared Radiation Signature TEIRS model.
- Infrared Detection and Detectors
- Jet and Gas Turbine Engines