This tutorial covers the propeller blade CLi curve. This curve defines the cross-section ideal lift coefficient along the blade for airfoil section types. For airfoils, this value is relatively straightforward since CLi is a common defining characteristic of these shapes or may be solved for using other parameters like camber. Other section types, such as ellipses or rectangles, do not have camber or similar features and so the CLi values at these stations will have no effect. Custom airfoil file (AF_File) types will NOT have their camber or CLi changed by the curve! For more information about how to manipulate these curves, please refer to the Propeller Blade Control Curve Interface page.
Note that the XSec values for camber or CLi are deactivated for propeller components as these values are controlled by the CLi curve! To apply a specific CLi at a given blade station, you must have a curve control point at that station and set the desired CLi.