aircraft:tmd:airfoil
Differences
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aircraft:tmd:airfoil [2017/03/06 11:28] – [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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'' | '' | ||
- | > 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 ===== | ||
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- | < | + | ></ |
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aircraft/tmd/airfoil.1488796088.txt.gz · Last modified: 2017/03/06 11:28 by jh