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A computer model of the Coanda/Refraction Jet Engine Test Cell facility was developed using the PHOENICS computer code. The PHOENICS code was utilized to determine the steady aerothermal characteristics of the test cell during the testing of an F404 gas turbine engine with afterburner in operation. Computer generated aerothermodynamic field variables of pressure, velocity and temperature parameters were compared to operational field test data. Observations regarding compared results as well as system behavior are presented. Additionally, recommendations of the applications of PHOENICS to future modeling projects are made.