Usually it's a quarter chord length from the leading edge of the airfoil. In addition the aerodynamic center does not change with variation in angle of attack.
The moment causing the aircraft to pitch down has negative sign and vice versa. It is in agreement with general right hand rule for moments f.e. in static analysis of cantilever beam (clockwise rotation has a negative sign...).
Thank you! This was very insightful!
Hi, can you help me with some questions, I am struggling on how to calculating cg margins on an aircraft?
how to find the aerodynamic center of the wing experimentally ?
Usually it's a quarter chord length from the leading edge of the airfoil. In addition the aerodynamic center does not change with variation in angle of attack.
What is the right hand rule the prof. is mentioning ?
The moment causing the aircraft to pitch down has negative sign and vice versa. It is in agreement with general right hand rule for moments f.e. in static analysis of cantilever beam (clockwise rotation has a negative sign...).
And maybe prof. probably recalls the right hand rule of gyroscopic effect for propeller