Model Manufacturing and Wind Tunnel Testing of High Lift System for SAT Aircraft
The scope of work is the experimental verification of the capabilities of innovative high lift systems solutions developed for SAT. For the purpose, a wind tunnel entry is needed including the design and manufacturing of wing segment models with selected high lift devices at meaningful Reynolds number. A complete set of experimental data, surface pressure and wake measurements shall be built to determine forces and moments in different high lift configurations. In particular, PIV technique will be requested to evaluate fluidic devices by comparison with CFD computations. Please refer to the full topic descriptions document published in this call.