[Zweeper]

Hello everybody!

I have a question about the reference values for an 3D multi element rear wing.

First of all, if i analyse a single element airfoil under different angles of attack, my reference area of my wing is always the chord-line times the length of the airfoil right? doesn't matter which angle of attack my airfoil has?!


But what happens in the case of an multi element rear wing? (attachment)
my logical thoughts say me that i just have to summarize all the single element areas by calculating the single elements as described above.

Is this right or i am doing an mistake there?


Kind regards!