Aileron control in flow separation...and elevator
I’m trying to get an appreciation of the relationship between max Cl and the amount of flow separation one can expect. For example, consider a wing with a constant chord, camber, and no wash out. Omit any external influences on the airflow (no fuselage, tip effects etc) and consider low speed flight to minimize compressibility effects.
Question 1; at maximum Cl, is there a general range of flow separation over the aft portion of the chord? Not looking for exact numbers, of course, but a number that can be considered reasonable. For example, aft 10-20% could be in separated flow.
Question 2: if there is some separated flow, then is it reasonable to expect for the wing conditions mentioned above (and at max Cl), that an aileron would experience a “snatch” to the up position?
Question 3; if the wing was at or above the stall angle of attack and the aileron is indeed “snatched” to the up position, is there any reason to believe that applying the aileron to the DOWN position would itself help RE ATTACH the flow (un stall the wing)?
These questions may sound strange, but the answers WILL lead somewhere, and I look forward to explaining further once I get some understanding of the above. Thanks for the replies, looking forward to all your thoughts. Stan