aircraft:tmd:airfoil
Differences
This shows you the differences between two versions of the page.
| Both sides previous revisionPrevious revisionNext revision | Previous revisionLast revisionBoth sides next revision | ||
| aircraft:tmd:airfoil [2018/09/20 12:03] – [Airfoil] jh | aircraft:tmd:airfoil [2019/07/07 10:49] – [Airfoil] jh | ||
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| Line 4: | Line 4: | ||
| === Other Aerodynamic classes === | === Other Aerodynamic classes === | ||
| - | [[aerowing]], | + | [[aerowing]], |
| ===== Angle of attack ===== | ===== Angle of attack ===== | ||
| Line 27: | Line 27: | ||
| 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. | ||
| - | < | + | < |
| - | | + | ></ |
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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