139KiB, 1196x543, airfoil.jpg
No.503390
High school inventor noob here. I was using NACA airfoils before, but then I found some problems that I don't know if are actually problems. The fact that the camber line is made from two parabolas that are pieced together at the point of maximum camber means that the two curves on the upper surface are only first degree smooth with each other. Same with the two curves on the lower surface. Also, the two curves that intersect at the leading edge are only second degree smooth with each other. I tried to make my own airfoil where the surfaces are made from one, continuously-changing spline, and the camber line is made from one spline with one vertex, to make it smoother.
My design was based on NACA airfoils, so the shape is described by the same variables, with the addition of the position of the maximum thickness on the chord, and the trailing edge thickness. This one has a max thickness of 10% of the chord, located at 30% of the chord's length from the leading edge, a max camber of 3% of the chord at 42.5% of the chord's length from the leading edge, and a trailing edge thickness of 2.5% of the maximum thickness.
What do you think? Any suggestions? Is there another airfoil I should consider researching maybe?