Abstract
In this paper the computational analysis and characterization of cockpit environmental control system (ECS) of a fighter aircraft is presented. ECS of the under study aircraft is designed for certain specific flight conditions in the aircraft flight envelope. Evaluation of ECS performance at the worst environmental condition is considered necessary for system verification. CFD techniques have been used to analyze the flow and temperature field inside the cockpit of an aircraft. The complete ECS performance has been evaluated for ISA + 30 o C atmospheric conditions for the worst case flight condition of M=0.825 at sea level, dry air properties. In addition to this, a transient analysis for engine at idle on ground has also been performed. The results of the present study indicate reasonable ECS performance with respect to relevant MIL standards.
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