aircraft:tmd:airfoil
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aircraft:tmd:airfoil [2017/03/02 11:19] – [Table of flap coefficients] jh | aircraft:tmd:airfoil [2020/09/28 22:44] (current) – jh | ||
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=== Other Aerodynamic classes === | === Other Aerodynamic classes === | ||
- | [[aerowing]], | + | [[aerowing]], |
===== Angle of attack ===== | ===== Angle of attack ===== | ||
- | The angle of attack (also known as AOA or α (" | + | The angle of attack (also known as AOA or α (" |
{{ Alpha.png? | {{ Alpha.png? | ||
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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? | ||
==== Cl0 ==== | ==== Cl0 ==== | ||
- | The '' | + | The '' |
> This attribute directly reflects the attitude in which an aircraft flies at high speed (low AOA). It also requires a larger down force from the horizontal stabilizer which increases the drag. It greatly affects the glide ratio. | > This attribute directly reflects the attitude in which an aircraft flies at high speed (low AOA). It also requires a larger down force from the horizontal stabilizer which increases the drag. It greatly affects the glide ratio. | ||
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==== CmAlpha ==== | ==== CmAlpha ==== | ||
- | The gradient of the momentum coefficient Cm is zero for symmetrical airfoils, positive for most typical airfoils that show movement of center of pressure (unstable) and negative for most airfoils with an s-bend (stable), used for flying wings. The '' | + | The gradient of the momentum coefficient Cm is zero for symmetrical airfoils, positive for most typical airfoils that show movement of center of pressure (unstable) and negative for most airfoils with an s-bend (stable), used for flying wings. The '' |
> The '' | > The '' | ||
> Typical '' | > Typical '' | ||
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==== Cm0 ==== | ==== Cm0 ==== | ||
- | '' | + | '' |
> With given geometry, incidence and fixed elevator position the '' | > With given geometry, incidence and fixed elevator position the '' | ||
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==== 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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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