Table of Contents

Honors Project

Results and Analysis

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.

pressure distrobution on NACA 2412 airfoil at 0 degrees
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.

true pressure distrobution @ 0 degrees
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.

calculated press. distrobution @ 10 degrees
Figure 6.The Modified NACA 2412 airfoil at a 10 angle of attack.


Next: Discussion

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