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The surface of many airfoils can be described with an equation of the form
where t is the maximum thickness as a fraction of the chord length c (e.g., tmax= 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.)
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Chapter 4 Solutions
EBK MATLAB: AN INTRODUCTION WITH APPLIC
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