This paper gives an overview of the interdisciplinary design process of an electrically-powered high-lift system for future commercial aircraft, with a focus on the mixed-flow compressor performance. Based on the requirements of the high-lift system, a multi-objective optimization is used for the aero-mechanical design of the compressor stage. The demand for high pressure ratio and efficiency, together with the constrained installation space yields an unconventional mixed-flow compressor design with a transonic flow regime. To supply the required pressurized air for the high-lift system, rotational speeds of up to60,000rpm are necessary according to CFD analysis. A very compact integrated prototype of the compressor system is designed, including electrical machine and power electronics with high power-to-mass ratios. Performance predictions are validated at part load. To integrate the compressor stage into the prototype, some adjustments to the geometry become necessary. Additional CFD simulations reveal a big impact of the new inlet duct on the compressor performance due to inlet flow distortion. It is assumed that a fully-integrated design process, which includes all relevant interdependencies of the different components, would yield a better overall system design.