Jul 27, 2022
Airfoil measurement and DAAD exchange program
Pressure distribution on a laminar airfoil with split flap (XFoil)
Within a DAAD exchange program, a student from the University of Nevada, Reno, currently works at the chair. He just finished his experimental task, which was to continue wind tunnel measurements on a wing with a laminar airfoil and a split flap.
Measuremet of lift and drag of a laminar wing with split flap
Subject of the recent investigations were additional flap positions above 50 degrees up to 75 degrees as well as various Reynolds numbers. Furthermore, attention was paid to potential unsteady effects when deploying the flap mid-flight and changing the angle of attack into stall and back. The most significant result is the increase of the maximum lift by about 20 lift counts due to the larger flap deflection.
Lift curves of the airfoil with split flap compared to the last campaign and to XFoil
Effect of changing the flap angle mid-stream