Differences

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

--- aircraft:tmd:airfoil [2017/03/02 11:13] – [Table of flap coefficients] jh
+++ aircraft:tmd:airfoil [2017/03/02 11:19] – [Table of flap coefficients] jh
@@ Line 110: / Line 110: @@
 ==== Table of flap coefficients ====
-> These are just examples, actual values may differ
+> These are total values, not the gradients needed for the Aerofly.
-^ Type of flap ^ ClFlap       ^ CdFlap          ^ CmFlap           ^
+^ Type of flap ^ Delta Cl Flap  ^ Delta Cd Flap   ^ Delta Cm Flap    ^
-| Plain flap   | 0.7 ... 1.5  | 0.005 ... 0.06  | -0.15 ... -0.7   |
+| Plain flap   | 0.7 ... 1.5    | 0.005 ... 0.06  | -0.15 ... -0.7   |
-| Split flap   | 0.7          | 0.18            | -0.19            |
+| Split flap   | 0.7            | 0.18            | -0.19            |
-| Slotted flap | 0.8 ... 2.0  | 0.06            | -0.14            |
+| Slotted flap | 0.8 ... 2.0    | 0.06            | -0.14            |
-| Fowler flap  | 1.4 ... 3.0  | 0.14 ... 0.3    | -0.73            |
+| 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 ====