I'm running the the stability calculations again for my design starting from the beginning using the Mechanics of Flight text by Phillips.
I must have been staring at it for too long or maybe its the time :tired: but for the life of me I cant figure out where he is getting the constant C subscript mt sigma e. (Cmtse)
Now I understand that it is the change in the pitching moment coefficient for the tailplane about the AC with respect to elevator deflection...
For a 0012 foil there is no change for the typical ranges of this foil, So could someone out there confirm for me that this would mean 0? It just seems too simple...
In his first example he gives a Cmtse=-0.55 and with my understanding, that would be huge?
I think its a dumb question with a simple answer... but its just one of those niggles I'd rather have some backup on.
Cheers
Justin
I must have been staring at it for too long or maybe its the time :tired: but for the life of me I cant figure out where he is getting the constant C subscript mt sigma e. (Cmtse)
Now I understand that it is the change in the pitching moment coefficient for the tailplane about the AC with respect to elevator deflection...
For a 0012 foil there is no change for the typical ranges of this foil, So could someone out there confirm for me that this would mean 0? It just seems too simple...
In his first example he gives a Cmtse=-0.55 and with my understanding, that would be huge?
I think its a dumb question with a simple answer... but its just one of those niggles I'd rather have some backup on.
Cheers
Justin
