That all makes sense. I wasn't sure if I was missing out any fudge factors anywhere along the line. Previous reports for the aircarft have given a pseudo stall at anywhere between 25kts (IAS) with power on and 31kts (IAS) at idle.
Bearing in mind that I'm new to all this, do vortex generators have the effect of increasing the Cl-max or is their performance improvement found elsewhere? I couldn't work out if they merely allow a steeper AoA and therefore a shift along the existing CL curve.
Also, by moving the C of G aft on a conventional aircraft I assume you keep the same CL but reduce the effective mass that the wing is supporting as it turns the tailplane into a lifting surface.
(Apologies for the poor use of terminology. Steeeep learning curve!)
Thanks for the calc, Mark 1. I guess I was in the right ballpark.
John Farley. I couldn't find anything published on how aspect ratio affected Cl-max but what you said makes sense.
PS At age 10, I wanted to be you when I grew up.
