User Tools

Site Tools

Trace:
aircraft:tmd:airfoil

Differences

This shows you the differences between two versions of the page.

Link to this comparison view

Both sides previous revisionPrevious revision
Next revision		Previous revision
Next revisionBoth sides next revision
aircraft:tmd:airfoil [2018/09/30 13:20] – [All] jhaircraft:tmd:airfoil [2018/09/30 13:21] – [ClAlpha] jh
Line 27: Line 27:
 The lift coefficient Cl and momentum coefficient Cm increase linear with alpha in the Range of ''-AttachedRange'' to ''+AttachedRange''.  The lift coefficient Cl and momentum coefficient Cm increase linear with alpha in the Range of ''-AttachedRange'' to ''+AttachedRange''. 
 The gradient of the lift coefficient in respect to alpha is ''ClAlpha'' which equals 2 * Math.Pi for most real airfoils.   The gradient of the lift coefficient in respect to alpha is ''ClAlpha'' which equals 2 * Math.Pi for most real airfoils.  
-> Leave it at ''6.28'' (2 * pi)+> Leave it at ''6.28'' (2 * pi) unless you are dealing with a delta wing
  
 {{ Airfoil_AttachedRange_ClAlpha.png?nolink }} {{ Airfoil_AttachedRange_ClAlpha.png?nolink }}
Line 146: Line 146:
 ==== Minimal ==== ==== Minimal ====
 This will fall back to default values for all attributes. This will fall back to default values for all attributes.
-<code>        <[string8][object][airfoil] +<code>            <[airfoil][AirfoilTip][] 
-            <[string8][Name][AirfoilTip]> +            ></code>
-        ></code>+
                  
 ==== All ===== ==== All =====
aircraft/tmd/airfoil.txt · Last modified: 2020/09/28 22:44 by jh