On Jan 25, 7:19 pm, Bertie the Bunyip wrote:
D Ramapriya wrote :



On Jan 25, 10:22 am, Pete Brown wrote:
If a conventional aircraft is in stable level flight and the stick is
pulled back, all of the texts I have read indicate that the aircraft
pitches up, rotating through the CG.

Is this exactly correct or is it a very useful approximation good for
all practical purposes?

Most aircraft have the CG located slightly forward of the center of
pressure ( CP or center of lift) for positive pitch stability. I was
wondering if the actual point of rotation is displaced somewhat aft
of the CG, someplace close to the CG but in fact some small distance
towards the CP.

When the aircraft is subject only to the force of gravity, any
displacement will cause it to rotate around the cg but in flight its
subject to gravity as well as the aerodynamic forces which act
through the CP, suggesting to me that the point of rotation is not
quite on the CG.

It's tempting to think that it could be somewhere near the center of
the balance arm but it's hard to logically argue against the CG, isn't
it?

They're the same thing.


By balance arm, I meant the distance between CG and CP. Missing
something, am I?

Ramapriya