NACA0012 Airfoil in Re=1x10^6 Viscous Airflow with Incidence Varied From -20 to 20 Degrees
, coefficients of lift, moment, and drag, the lift to drag ratio, and some other "critical" value that is considered constant (at the time of this typing I forget what it is, for the assignment I was mostly only concerned with the lift coefficient). This was done using XFOIL, a airfoil analysis program developed by Mark Drela at MIT. (web.mit.edu It was for Prof. Chattot's "Applied Aircraft Aerodynamics" class (EAE 127) at the University of California at Davis. ... airfoil aiflow xfoil ...
