(20 points) Consider a prismatic (unswept), thin-walled NACA 0015 airfoil (uncambered) of chord c. It is...

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(20 points) Consider a prismatic (unswept), thin-walled NACA 0015 airfoil (uncambered) of chord c. It is made of uniform sheet aluminum (thickness t) with no internal spars. T 0.15c N C + -y (a) Look up the equation for the airfoil surface (see Abbot & Von Doenhoff or Wikipedia). (b) Determine the torsion constant, J, in terms of the given parameters. (This can be done numerically.) (20 points) Consider a prismatic (unswept), thin-walled NACA 0015 airfoil (uncambered) of chord c. It is made of uniform sheet aluminum (thickness t) with no internal spars. T 0.15c N C + -y (a) Look up the equation for the airfoil surface (see Abbot & Von Doenhoff or Wikipedia). (b) Determine the torsion constant, J, in terms of the given parameters. (This can be done numerically.)