[15 pts] In the book and presentations, we used dimensional analysis to derive the expression . Now use dimensional analysis to derive .
[20 pts] Use the following airfoils from the back of the book (Appendix D): NACA 1412, NACA 2412, NACA 4412, NACA 0006, and NACA 0009. For this question, use the airfoil data that is closest to a Reynolds number of 6 million. Make sure you are using the correct curve. Do not use the “Standard roughness” or flap curves.
For each airfoil, what is the maximum percent camber, the location of the maximum camber, and the maximum percent thickness? Using the airfoil data in the back of the book, what is the , at , and at for each airfoil? From the information in (b), what can you say about the effect of camber? What is special about the lift and moment for the symmetric airfoils? For the symmetric airfoils, use the data in the back of the book to find and . From the information in (d), what is the effect of thickness on the lift curve?