My generalized wing was not meant to have any specifically designed aerodynamics to prevent aileron snatch, nor enhance laminar flow. For example, a simple NASA 2412 airfoil. For airflow separation, I wasn’t thinking necessarily about non laminar flow, but more along the lines of when the angle of attack is at the stall, so that neither the turbulent boundary layer nor any of the remaining laminar flow can actually stay attached to the complete upper surface.
For example, past pictures of a “stall” sometimes show tufts of wool or cotton streamlined back on the upper surface, but for those near the trailing edge I think they were no longer “streamed”, and were often even pointing forward. I don’t have a reliable source for this, so I’ll try to make this question a bit simpler:
Would it be correct to say that GENERALLY for the simple situation I posted originally, if this wing is at an aoa that it is just stalled, can we expect some flow separation on the aft 20% OR SO of the chord, and hence cause an up force on the aft section of the chord due to pressure differential between surfaces?
Thanks for being the first responder Guppy. I’m not sure if you were answering YES, or NO, to my questions.
Stan