Originally Posted by
mavisbacon
Lift = 1/2. Cl. Rho.Vsq.S it's the Cl bit that changes (I fink)
try L=Cl (1/2rhoVsq)S
lodown is just abusing bernoulli
i have video proof of bernoulli in action over a wing. and i don't think it should be explained as the 'low pressure lifting the wing', (at a very basic level) more that the higher px is trying to move to the low px area, but the wing is in the way - that conveniently explains spanwise flow nicely too
here's what i reckon:
the average chord will change with split flap, but angle of attack should remain the same, just at a lower IAS, for the same nose attitude as the higher IAS. no different than extending 'simple' flap really.