For the development of new performance parameters of high lift configurations for future aircrafts with active flow control, compact, dynamic and lightweight compressor systems need to be provided, driven by high performance electrical motors preferably located in the wings. These compressor systems need power densities and operating ranges that exceed the current state of the art, and they will be placed as close as possible to the slots for active flow control. In addition, a fast control of the systems must be ensured. In order to achieve these goals, aerodynamic techniques for the compact design of the compressor by the use of variable-geometry devices and fundamentals of new methods of multipoint optimization will be investigated in this project.