I meant the airflow from the slat goes over the LE of the wing and over the upper surface and does not flow allong the bottom surface of the wing. (at High AoA, as seen in the diagrams)
up to point of stall ALL airflow moves over top and bottom surface of the wing. It MUST do so in order to obtain lift. Theoretically speaking, two 'tubes' of freestream air which hits leading edge stagnation point, split and must reach trailing edge stagnation point at same time.
Use a Clark Y for easy illustration - The tube over the top surface must travel faster over the top surface to reach the trailing edge at the same time... therefore ----> higher velocity (lower pressure than freestream) and also higher velocity than the bottom tube velocity.
Not to start this whole argument up again, but the article
virtualpilots.fi: 109myths which has the second diagram seems refer to "liftloading" (note, no space) in the context Soren was using it. I then did another google search of "liftloading" and found several other refrences to the term (all as one word) that seem to match Soren's usage. (the majority of which seem to be referring to the BF 109)
KK - the author of "Why Kit Carson Was an Idiot" article appears to have the same academic background in Aerodynamics as Soren - at least he seems contemptuous of any academics that Kit Carson brought to the table with the following comments
They found out that the proposed "washout" did not help but made the stall characteristics worse! Yes, Mr. Carson, it made it worse!! Germans and Willy DID know about washout! So take you poor schoolar knowledge you learned from some books and :/$/"§$!"§$ !!!
Hard to make a case that his 'theory' about liftloading is based on any theoretically sound basis. BTW you notice that his result is in #/Ft^2 which is 'implied' as a lift loading.
In fact, Lift/Clmax = 1/2*rho*V^2 ---> which SPECIFICALLY is 'q" , the freestream dynamic pressure and has ZERO relevance to 'lift loading' in this context and everything to do with freestream Velocity
This particular article could also be where Soren came up with the idea of 'Lift loading' as an expression of WL/Clmax
Why Carson was an idiot
This one in particular uses it in Soren's exact context. (additionally the Clmax figures seem much lower than what I've seen for the listed a/c)
see above
QUOTE]
KK-
Cl has only one source in Aerodynamics. It is
Cl = Lift/(1/2*rho*V^2 x Wing Area)
Using Cl in any equation brings the dynamic pressure expression into the calculation. Period.