aircraft:tmd:airfoil
Differences
This shows you the differences between two versions of the page.
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aircraft:tmd:airfoil [2018/09/20 12:03] – [Airfoil] jh | aircraft:tmd:airfoil [2018/09/30 13:21] – [ClAlpha] jh | ||
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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? | ||
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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. | ||
- | < | + | < |
- | | + | ></ |
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==== All ===== | ==== All ===== | ||
- | < | + | < |
- | <[string8][Name][AirfoilTip]> | + | < |
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- | < | + | ></ |
- | ></ | + | |
aircraft/tmd/airfoil.txt · Last modified: 2020/09/28 22:44 by jh