Cl aoa and stalling angle Help
Regarding to critical angle of attack and stall...
For a given aerofoil... does the stalling angle change (provided flaps are up) ofcourse...
I know the stallin speed changes and is affected by many things sucb as weight, load factor, etx etc etc. But does the stalling angle given for a specific aerofoil change? Or is it fixed and once exceeded it will stall? Is it true in regards to larger jet aircraft?
The graph CL over AOA is given to a specific aerofoil and thus aircraft type ... but does that mean it is at that one speed ? Is that graph true for cruising speed? Or thru out the whole speed for that aircraft and weight...
I was told because CL is affected by speed and Reynolds number the stalling angle cannot be fixed for a specific aerofoil thus it is variable....