User:Eas4200c.f08.carbon.orear/HW3/Matlab

= Code =

NACAairfoil.m
Note: The code is currently unable to calculate the centroid. This issue is being debugged and resolved presently. Check back to the live page at a later time for this calculation and the appropriate debug section.

AirfoilArea.m
= Debugging =

Circle
With a circular airfoil, the Number of Segments such that the computed Area of the airfoil is accurate to within 1% of the exact value is 23 segments at which the computed area was 3.1115 m3. This is 0.95% away from the actual area of a unit circle, 3.14195 m3.

Code used to find ns_max



The area for a various number of segments is tabulated below.

Plotting the Area vs Number of segments up to the point of 1% accuracy we get the graph below.

At P0 = (0,0), Area computed equaled 3.1115

At P0 = (1,0), Area computed equaled 3.1115

At P0 = (1,-4), Area computed still equaled 3.1115

NACA Airfoil
With a circular airfoil, the Number of Segments such that the computed Area of the airfoil is accurate to within 1% of the previous value is 8 segments at which the computed area was 0.024616 m3. This is 0.77% away from the previous area of a unit circle, 0.024373 m3. At 10,000 segments, the computed area was 0.02569 m3.

Code used to find ns_max



The area for a various number of segments is tabulated below.

Plotting the Area vs Number of segments up to the point of 1% difference accuracy we get the graph below.

At P0 = (0,0), Area computed equaled 0.024616

At P0 = (.25, 0), Area computed equaled 0.024616

At P0 = (.25,-1), Area computed still equaled 0.024616