The development of modern military aircraft has to meet considerable requirements in terms of reducing the system weight, installation space, as well as radar signature. For fighter aircraft, serpentine intakes are commonly used since they reduce the radar visibility of the engine, the system weight, and allow the optimal use of the installation space. However, these intake systems cause flow disturbances for the engine. To avoid penalties in engine performance, active flow control methods can be implemented for controlling the flow through the intake. The experiments undertaken at the Institute of Jet Propulsion (ISA) at the Bundeswehr University Munich used a scaled model of a compact double s-shaped intake duct with flow control techniques utilizing air injection and suction for boundary layer control and separation suppression. Detailed total pressure measurements with a Kiel probe rake at the exit plane of the duct show the effectiveness of the individual flow control mechanisms. Suction is applied at three different locations. For each configuration, the suction port diameter and mass flow rate are varied. For tests with injection, air is blown into the intake duct through a Coanda nozzle at two specific positions. The Coanda nozzle slot width and the number of slots were varied. The results demonstrate which parameters must be set to effectively influence the flow and achieve favorable distortion parameters at the intake duct’s outlet.