aircraft:tmd:airfoil
Differences
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Both sides previous revisionPrevious revisionNext revision | Previous revisionLast revisionBoth sides next revision | ||
aircraft:tmd:airfoil [2018/09/30 13:20] – [All] jh | aircraft:tmd:airfoil [2019/07/07 10:49] – [Airfoil] jh | ||
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=== Other Aerodynamic classes === | === Other Aerodynamic classes === | ||
- | [[aerowing]], | + | [[aerowing]], |
===== Angle of attack ===== | ===== Angle of attack ===== | ||
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The lift coefficient Cl and momentum coefficient Cm increase linear with alpha in the Range of '' | The lift coefficient Cl and momentum coefficient Cm increase linear with alpha in the Range of '' | ||
The gradient of the lift coefficient in respect to alpha is '' | The gradient of the lift coefficient in respect to alpha is '' | ||
- | > Leave it at '' | + | > Leave it at '' |
{{ Airfoil_AttachedRange_ClAlpha.png? | {{ Airfoil_AttachedRange_ClAlpha.png? | ||
Line 127: | Line 127: | ||
'' | '' | ||
- | > The lower the value of '' | + | > The lower the value of '' |
{{ Airfoil_Stall_ClAlphaBase.png? | {{ Airfoil_Stall_ClAlphaBase.png? | ||
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==== Minimal ==== | ==== Minimal ==== | ||
This will fall back to default values for all attributes. | This will fall back to default values for all attributes. | ||
- | < | + | < |
- | | + | ></ |
- | | + | |
| | ||
==== All ===== | ==== All ===== |
aircraft/tmd/airfoil.txt · Last modified: 2020/09/28 22:44 by jh