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 11:21] – [CmAlphaBase] jh | aircraft:tmd:airfoil [2018/09/30 13:20] – [Minimal] jh | ||
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| === Other Aerodynamic classes === | === Other Aerodynamic classes === | ||
| - | [[aerowing]], | + | [[aerowing]], |
| ===== Angle of attack ===== | ===== Angle of attack ===== | ||
| 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: | ||
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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