Code: Select all
<function name="aero/coefficient/CLDe">
<description>Lift_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.4300</value>
</product>
</function>
Let's say I agree with this, and that it's convention to use the wing area to calculate the additional lift generated by the elevator.
the difference in area between the wing and tail is a ratio of 4.54.... so if we were to use the tail area the Cl value of 0.43 would have to rise to 1.922 to produce the equivalent force. That seems a rather large 'additional' Cl...
So now lets look at the drag for the elevator...
Code: Select all
<function name="aero/coefficient/CDDe">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/mag-elevator-pos-rad</property>
<value>0.0000</value>
</product>
</function>
Ooops no drag effect of elevator deflection.... that's a serious Lift 2 Drag ratio.
I don't think this is correct.
Simon