According to NACA report 648 I have made a little excel sheet to cuantify the downwash angle on the tail for a plane with 30% slotted flaps over 70% of the semispan.
I got the following numbers:
No Flaps AoA=0º (Cl=0,1) Downwash Angle 1.18º
No Flaps AoA=12º (Cl=1.2) Downwash Angle 7.1º
Flaps Extended 40º AoA=12º (Cl=2.4) Downwash Angle 14.21º
Do you think I have interpreted the paper correctly?
I got the following numbers:
No Flaps AoA=0º (Cl=0,1) Downwash Angle 1.18º
No Flaps AoA=12º (Cl=1.2) Downwash Angle 7.1º
Flaps Extended 40º AoA=12º (Cl=2.4) Downwash Angle 14.21º
Do you think I have interpreted the paper correctly?
