The objective of this study is to investigate on an experimental basis the influence of different inlet distortions on the operational characteristics of a twin-spool turbofan engine representing a propulsion system application of a military aircraft. The inlet duct of a supersonic aircraft is a very sensitive component and plays a dominant role with respect to engine and aircraft performance. Its very complex shape,containing a S-duct,creates total pressure and swirl distortions and leads to an inhomogeneous air stream in the compressor inlet plane.
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