Appendix A Geometry for Aerodynamicists
Appendix A: Geometry A-5 10/23/97 An example: NACA 23012, is a 12% thick airfoil, the design lift coefficient is 0.3, the position of max camber is located at x/c = 0.15, and the “standard” 5 digit foil camber line is used. The thickness distribution is the same as the NACA 4 digit airfoil thickness distribution described above in equation ...
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