@inbook{doi:10.2514/6.2019-3170,
  author = {Devansh Agrawal and Faisal Asad and Blake M. Berk and Trevor Long and Jackson Lubin and Christopher Courtin and Mark Drela and R John Hansman and Jacqueline L. Thomas},
  title = {Wind Tunnel Testing of a Blown Flap Wing},
  booktitle = {AIAA Aviation 2019 Forum},
  chapter = {},
  pages = {},
  doi = {10.2514/6.2019-3170},
  URL = {https://arc.aiaa.org/doi/abs/10.2514/6.2019-3170},
  eprint = {https://arc.aiaa.org/doi/pdf/10.2514/6.2019-3170}
}

This paper presents wind tunnel measurements of blown flapped airfoil performance forapplication to distributed electric propulsion STOL aircraft. The 2D airfoil wind tunnelmodel features a simple slotted flap, and closely-spaced spanwise-distributed propellers drivenby electric motors. Measurements of lift, pitching moment and net streamwise force (dragminus thrust) were made over a range of propeller RPM, angle of attack and flap angle. Liftcoefficients up to 9 were measured for practical blowing levels. High lift was also measuredwith net streamwise force close to zero, which suggests that the use of blown lift during landingis practical.