Differences

This shows you the differences between two versions of the page.

--- aircraft:tmd:airfoil [2018/09/30 13:20] – [Minimal] jh
+++ aircraft:tmd:airfoil [2018/09/30 13:21] – [ClAlpha] jh
@@ Line 27: / Line 27: @@
 The lift coefficient Cl and momentum coefficient Cm increase linear with alpha in the Range of ''-AttachedRange'' to ''+AttachedRange''.
 The gradient of the lift coefficient in respect to alpha is ''ClAlpha'' which equals 2 * Math.Pi for most real airfoils.
-> Leave it at ''6.28'' (2 * pi)
+> Leave it at ''6.28'' (2 * pi) unless you are dealing with a delta wing
 {{ Airfoil_AttachedRange_ClAlpha.png?nolink }}