Chapter 4, Problem 25P

The surface of many airfoils can be described with an equation of the form

$y=\pm \frac{tc}{0.2}\left[a_0\sqrt{x/c}+a_1(x/c)+a_2{(x/c)}^2+a_3{(x/c)}^2+a_4{(x/c)}^4\right]$

where t is the maximum thickness as a fraction of the chord length c (e.g., t_max= ct). Given that c = 1m and t = 0.2m, the following values for v have been measured for a particular airfoil:

x(m)	0.15	0.35	0.5	0.7	0.85
y(m)	0.08909	0.09914	0.08823	0.06107	0.03421

Determine the constants a₀, a₁, a₂, a₃, and a₄. (Write a system of live equations and five unknowns, and use MATLAB to solve the equations.)