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JSBSim Aerodynamics: Difference between revisions
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| Line 54: | Line 54: | ||
<table > | <table > | ||
<independentVar lookup="row">aero/alpha-rad</independentVar> | <independentVar lookup="row">aero/alpha-rad</independentVar> | ||
<tableData> | <tableData> | ||
0.26 0.26 | 0.26 0.26 | ||
-0.26 -0.26 | -0.26 -0.26 | ||
</tableData> | </tableData> | ||
</table> | </table> | ||
Beyond +/- | |||
Beyond +/- 22.5 degrees AoA we'll use 0.26 * sin(2*AoA) to approximate lift, and linear interpolate between 15 and 22.5 degrees AoA. (These numbers are rather arbitrary.) The resultant table returns the same value as alpha-rad for the "stable" flight regime so the function will accept the [[aeromatic]] coefficient. Outside of the "stable" flight regime a better number will be used allowing more realistic flight behavior at high alpha or beta angles. | |||
<table > | |||
<independentVar lookup="row">aero/alpha-rad</independentVar> | |||
<tableData> | |||
-3.14 0.0 | |||
-2.62 0.2252 | |||
-2.36 0.26 | |||
-2.09 0.2252 | |||
-1.57 0.0 | |||
-1.05 -0.2252 | |||
-0.79 -0.26 | |||
-0.52 -0.2252 | |||
-0.39 -0.1838 | |||
-0.26 -0.2588 | |||
0.0 0.0 | |||
0.26 0.2588 | |||
0.39 0.1838 | |||
0.52 0.2252 | |||
0.79 0.26 | |||
1.05 0.2252 | |||
1.57 0.0 | |||
2.09 -0.2252 | |||
2.36 -0.26 | |||
2.62 -0.2252 | |||
3.14 0.0 | |||
</tableData> | |||
</table> | |||
This table can drop directly into an [[aeromatic]] [[FDM]] to replace an instance of aero/alpha-rad or aero/beta-rad (changing the independent var of course). | |||