aircraft:tmd:airfoil
Differences
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Both sides previous revisionPrevious revisionNext revision | Previous revisionNext revisionBoth sides next revision | ||
aircraft:tmd:airfoil [2017/03/02 11:10] – jh | aircraft:tmd:airfoil [2017/03/06 11:28] – [Table of flap coefficients] jh | ||
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{{ Airfoil_AttachedRange_CdAlpha.png? | {{ Airfoil_AttachedRange_CdAlpha.png? | ||
- | ==== Flaps ==== | + | ==== AttachedCenterFlap |
- | === AttachedCenterFlap | + | |
The '' | The '' | ||
> Leave it at '' | > Leave it at '' | ||
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> Set a value that is lower to increase the effect of reversed ailerons near stall. | > Set a value that is lower to increase the effect of reversed ailerons near stall. | ||
- | === ClFlap === | + | ==== ClFlap |
'' | '' | ||
> '' | > '' | ||
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{{ Airfoil_AttachedRange_ClFlap.png? | {{ Airfoil_AttachedRange_ClFlap.png? | ||
- | === CmFlap === | + | ==== CmFlap |
'' | '' | ||
> Some aircraft need tremendous amount of negative '' | > Some aircraft need tremendous amount of negative '' | ||
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{{ Airfoil_AttachedRange_CmFlap.png? | {{ Airfoil_AttachedRange_CmFlap.png? | ||
- | === CdFlap === | + | ==== CdFlap |
'' | '' | ||
> Real life flaps always create additional drag when deflected. '' | > Real life flaps always create additional drag when deflected. '' | ||
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> | > | ||
- | <div id = " | ||
==== Table of flap coefficients ==== | ==== Table of flap coefficients ==== | ||
- | > These are just examples | + | Recommended values for the Aerofly |
- | ^ Type of flap ^ ClFlap | + | ^ Type of flap ^ ClFlap |
- | | Plain flap | + | | Plain flap |
- | | Split flap | + | | Split flap |
- | | Slotted flap | 0.8 ... 2.0 | + | | Slotted flap | 2.7 | 0.06 |
- | | Fowler flap | 1.4 ... 3.0 | 0.14 ... 0.3 | -0.73 | + | | Fowler flap | 2.7 ... 3.4 | 0.2 |
- | </ | + | |
- | ==== StallRange and beyond | + | ==== ClAlphaBase |
- | + | ||
- | === ClAlphaBase | + | |
The lift coefficient can be approximated with a sinus function with the wave length of '' | The lift coefficient can be approximated with a sinus function with the wave length of '' | ||
'' | '' | ||
> Decrease this value to get a greater wing drop in a stall and during spins. Lower values increase the dynamics of accelerated stalls and maneuvers. Also decrease CdAlphaBase. | > Decrease this value to get a greater wing drop in a stall and during spins. Lower values increase the dynamics of accelerated stalls and maneuvers. Also decrease CdAlphaBase. | ||
- | === CmAlphaBase === | + | ==== CmAlphaBase |
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? | ||
- | === ClFlapBase === | + | ==== ClFlapBase |
The '' | The '' | ||
> Use the value to regulate the control surface authority in stall or at a high deflection angle. This increases the roll rate for aerobatic airplanes. (See '' | > Use the value to regulate the control surface authority in stall or at a high deflection angle. This increases the roll rate for aerobatic airplanes. (See '' | ||
- | === CdAlphaBase === | + | ==== CdAlphaBase |
The drag coefficient can be approximated with a sin^2 (sinus squared) function that repeats every '' | The drag coefficient can be approximated with a sin^2 (sinus squared) function that repeats every '' | ||
> Decrease the '' | > Decrease the '' |
aircraft/tmd/airfoil.txt · Last modified: 2020/09/28 22:44 by jh