The surface of many airfoils can be described with an equation of the form
y = ˆ“ tc/0.2 [a0ˆšx/c + a1 (x/c) +
+ a2(x/c)2 + a3(x/ c)3 + a4(x/c)4]
where t is the maximum thickness as a fraction of the chord length c (e.g., tmax = ct ). Given that c = l m and t = 0.2 m, the following values for y have been measured for a particular airfoil:

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

Transcribed Image Text:

x (m)0.50.35 0.5 0.7 0.85 y (m0.08909 0.09914 0.08823 0.06107 0.03421