Pitching moment on Flap Extension
Hey guys,
I have a question regarding the associated Pitching-moment with Flap Extension.
In my opinion to answer a question like "What pitching-moment will a Flap Extension cause?" I need to know where the CP in relation to the CG on that particular aircraft is.
If the CP is aft of the CG, then a flap extension should cause a pitch down even with the increased downwash which is reducing the AOA of the horizontal stabilizer?
Furthermore, I think that the CP of airliner usually is aft of the CG to have a positive longitudinal stability?
Maybe one of you can clarify..
Thanks!