User:Eas4200c.f08.aeris.holladay

HW: Airfoil Matlab Code
For this homework assignment, our task was to modify the airfoil code from the last homework to make it work for multi-cell airfoils. The airfoil was to be divided at a quarter chord ($$c/4$$) and three-quarter chord ($$3c/4$$). The profile of the airfoil from last homework is shown below.

$$\bar{A}=0.0253 m^2$$ For this week we split the airfoil into three cells. The new profile for the airfoil is shown below.

$$\bar{A_{1}}=0.0096 m^2$$ $$\bar{A_{2}}=0.013 m^2$$ $$\bar{A_{3}}=0.0027 m^2$$ The code had to be modified to calculate the area for each cell. To calculate the area for cell 1, we first found the closest location of $$y=c/4$$. Using the cross-product of two position vectors we were able to calculate the area to the leading edge of the airfoil. Next we calculated the area for cell 3 using a similar procedure. After finding the point of $$y=3c/4$$ we were able to calculate the area to the trailing edge. For cell 2 we took the total area and subtracted cells 1 and 3.