aircraft:tmd:airfoil
Differences
This shows you the differences between two versions of the page.
Both sides previous revisionPrevious revisionNext revision | Previous revisionNext revisionBoth sides next revision | ||
aircraft:tmd:airfoil [2017/03/02 11:19] – [Table of flap coefficients] jh | aircraft:tmd:airfoil [2017/03/06 11:28] – [Table of flap coefficients] jh | ||
---|---|---|---|
Line 109: | Line 109: | ||
==== Table of flap coefficients ==== | ==== Table of flap coefficients ==== | ||
- | |||
- | > These are total values, not the gradients needed for the Aerofly. | ||
- | |||
- | ^ 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 | | ||
- | | Split flap | 0.7 | 0.18 | -0.19 | | ||
- | | Slotted flap | 0.8 ... 2.0 | 0.06 | -0.14 | | ||
- | | Fowler flap | 1.4 ... 3.0 | 0.14 ... 0.3 | -0.73 | | ||
Recommended values for the Aerofly are: | Recommended values for the Aerofly are: | ||
Line 134: | Line 126: | ||
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. | 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. | ||
'' | '' | ||
+ | |||
+ | > The lower the value of '' | ||
{{ Airfoil_Stall_ClAlphaBase.png? | {{ Airfoil_Stall_ClAlphaBase.png? |
aircraft/tmd/airfoil.txt · Last modified: 2020/09/28 22:44 by jh