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 [2017/03/02 11:12] – [Table of flap coefficients] 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? | ||
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| ==== Table of flap coefficients ==== | ==== Table of flap coefficients ==== | ||
| - | > These are just examples | + | Recommended values for the Aerofly |
| - | + | ||
| - | ^ Type of flap ^ ClFlap | + | |
| - | | 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 | | + | |
| + | ^ Type of flap ^ ClFlap | ||
| + | | 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 ==== | ==== ClAlphaBase ==== | ||
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| 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? | ||
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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 ===== | ||
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aircraft/tmd/airfoil.txt · Last modified: 2020/09/28 22:44 by jh