i want to the matlab code for a numerical nonlinear lifting line method in aerodynamcis.

AR=10 , chord =1 and the wing is rectangular wing.

plz show me how to describe equation 5.76 in picture as matlab code.

3. With this assumed variation of , calculate the induced angle of attack i from Equation (5.18) at each of the stations: i(yn)=4V1b/2b/2yny(d/dy)dy The integral is evaluated numerically. If Simpson's rule is used, Equation (5.75) becomes i(yn)=4V13yj=2,4,6k(ynyj1)(d/dy)j1+4ynyj(d/dy)j+ynyj+1(d/dy)j+1 where y is the distance between stations. In Equation (5.76), when yn=yj1,yj, or yj+1, a singularity occurs (a denominator goes to zero). When this singularity occurs, it can be avoided by replacing the given term by its average value based on the two adjacent sections. 4. Using i from step 3, obtain the effective angle of attack eff at each station from eff(yn)=i(yn) 5. With the distribution of eff calculated from step 4 , obtain the section lift coefficient (cl)n at each station. These values are read from the known lift curve for the airfoil. 6. From (cl)n obtained in step 5 , a new circulation distribution is calculated from the Kutta-Joutition of lift coefficient