![]() When the program tries to do reverse engineering from reading XYZ surface coordinates creating a meanline format, the uncertainty grows larger. For example, the gap of geometry between those two airfoil definitions can be illustrated below for a blade, near the leading-edge, on any surface of revolution in the spanwise direction.įor a given normal thickness of (Tn) at a streamwise point (i) along camberline, the gap or deviation of geometry between the two airfoil definitions can be easily identified (as Delta) which cannot be ignored especially in case of high camber. ![]() Below is my summary for them.ĭepending on where the perpendicular condition is imposed, either at camberline or at surfaces, two different shapes of the airfoil will be created under the same normal thickness. I have no idea of what airfoil definition the current every commercial design program was built on, between two kinds of definitions for an airfoil. Many commercial programs, including my BLADE3DR, follow the way of approach, but when we dig into details of the methods we will realize how tricky they are depending on airfoil definitions. Meridional flowpath contours on the hub and the shroud.In the blade 3D design step, the most popular way of building shapes is to combine the spanwise distributions of the following 3 geometric parameters from blade leading-edge to trailing-edge :
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