Flying Wing Airfoil Data at Low Reynolds Numbers
XFOIL Predictions

Kelly O'Brien (kjobrien@uiuc.edu)
Department of Aeronautical and Astronautical Engineering
University of Illinois at Urbana-Champaign, Urbana, Illinois 61801

Last update 2/13/97

The following airfoils were analyzed at Reynolds numbers of 100k 200k, 400k, 600k and 2000k using XFOIL written by Prof. Mark Drela, MIT.

Each link displays two graphs:
1] the x vs. Cp plot at Cl=0.65 and Re=200k
2] the combined Cd vs Cl plot at each Reynolds number.
Sorry, no tabulated data is available.