Search results with tag "Aerodynamicists"

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 ...

  Design, Appendix, Geometry, Appendix a geometry for aerodynamicists, Aerodynamicists