The VENUS project is aimed to develop methods and tools enabling a concurrent aerodynamic and aeroacoustic design of a distributed electric propulsion configuration aircraft. As a practical achievement, the study will support the design of a new regional aircraft configuration, in terms of wing and engines’ installation, optimized in terms of aerodynamic and aeroacoustic performance. All the produced models, data and documents will be open access for other institutions, in order to establish an ”open test-case” for the whole European scientific community, unique in the aircraft design landscape. A wing model equipped with a flap and three propellers powered by electric motors will be tested in the Pininfarina wind tunnel. Acoustic, aerodynamic and wall pressure measurements will be carried out. The propeller geometry is obtained through an aeroacoustic optimization, with aerodynamic constraints. An optimized acoustic liner is installed on the wing for acoustic mitigation. The parameters to be changed during the tests include five blade pitch settings, an angle of attack sweep, take-off and landing flap configurations, phase shift between the propellers, different relative distances between the propellers and with respect to the wing. The final step will consist in the assessment of the numerical models based on experimental data.