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The full integration of the propulsion system is an important requirement for military aircraft in order to reduce their radar signature and to increase overall aerodynamic performance. This leads to short and highly bent engine intake ducts, which typically provoke severe flow distortions close to the compressor system. Especially in compact systems the flow within both the intake duct and the compressor interacts. In the last decades the intake duct and the compressor system have predominantly been designed separately . Nevertheless, the aerodynamic intake - compressor interactions have to be considered during the design of highly compact and thus aerodynamically coupled propulsion systems . The Institute of Jet Propulsion at the Bundeswehr University Munich hence developed a military engine intake duct specifically for research purposes. The research duct can be tested in both a remote - and close - coupled configuration with the Larzac 04 turbofan engine. Different types of adapters integrated within the duct ’s structure enable extensive wall pressure measurements and moreover a flexible integration of flow control devices. This paper evaluates the commissioning of the research duct in several configurations. It is focused on, first, the initial design o f a passive flow control device, which serves as base design for further studies on flow control in the research duct. Second, time - resolved static wall pressure measurements at various positions reveal the unsteady character of the flow within the range of 0 . 21 < St < 0.26 , which is most probably relate d to a mass flow fluctuation