Below you see a figure of a flying wing, so an aircraft without a tail. Its centre of gravity is situated behind the aerodynamic centre of the wing, with l(cg)=0.05c. If you are given that the wing flies with C_L =0.8and given that C_=0.02, determine the moment coefficient of the moment around the aerodynamic centre.

Answer 1

To determine the moment coefficient (Cm) around the aerodynamic center, we can use the equation:

Cm = (C_L)*(X_cg - X_ac)/c

Where:
- Cm is the moment coefficient
- C_L is the lift coefficient (0.8 in this case)
- X_cg is the distance from the aerodynamic center to the center of gravity (0.05c in this case)
- X_ac is the distance from the reference point (usually the leading edge of the wing) to the aerodynamic center
- c is the chord length of the wing

Since the figure given doesn't specify the distance X_ac, we can't calculate the moment coefficient without that information.