Differences

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

--- aircraft:tmd:airfoil [2017/03/02 11:15] – [Table of flap coefficients] jh
+++ aircraft:tmd:airfoil [2017/03/02 11:21] – [CmAlphaBase] jh
@@ Line 118: / Line 118: @@
 | Fowler flap  | 1.4 ... 3.0    | 0.14 ... 0.3    | -0.73            |
+Recommended values for the Aerofly are:
+^ Type of flap ^ ClFlap      ^ CdFlap   ^ CmFlap         ^
+| Plain flap   | 2.1         | 0.0      | -0.2 ... -0.5  |
+| Split flap   | 2.4         | 0.2      | -0.2 ... -0.9  |
+| Slotted flap | 2.7         | 0.06     | -0.2           |
+| Fowler flap  | 2.7 ... 3.4 | 0.2      | -0.6 ... -1.1  |
 ==== ClAlphaBase ====
@@ Line 127: / Line 134: @@
 Follows the same principle as the ClAlphaBase attribute. Usually this value is negative and the airfoil creates a pitch down force when the angle of attack increases beyond the stall angle (stable). The aircraft will pitch down on its own and accelerate again. A positive value is destabilizing.
 ''ClAlphaBase'' is usually the maximum momentum coefficient an airfoil will ever create.
+> The lower the value of ''ClAlphaBase'' the more the nose will drop when approaching a stall. Values near ''-0.2'' tend to soften the stall behavior.
 {{ Airfoil_Stall_ClAlphaBase.png?nolink }}