Once the source-paneling program was written, its results were carefully checked against those found in the source-paneling example in Fundamentals of Aerodynamics for the case of a sphere.
Once this worked, the NACA 2412 airfoil was slightly modified for use in the program, and then its results were examined.
Figure 4. Pressure coefficient distribution for the modified NACA 2412 airfoil at 0° angle of attack.
It is painfully obvious that this is not very accurate, but just to drive this further, the real result is pictured in figure 5.
Figure 5. The NACA 2412 airfoil's true pressure distribution at no angle of attack.
Finally, the modified NACA 2412 airfoil is further analyzed at a "critical angle of attack", which was picked to be 10°.
Figure 6.The Modified NACA 2412 airfoil at a 10° angle of attack.
© 2006 Nic Reveles