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=0.8 and given that C_m=0.02, determine the moment coefficient of the moment around the aerodynamic centre.

Question

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=0.8  and given that C_m=0.02, determine the moment coefficient of the moment around the aerodynamic centre.

GPT 3.5 · Answer

To determine the moment coefficient around the aerodynamic centre (C_mac), we can use the equation:

C_mac = C_m - (l_cg / MAC) * C_l

Where:
- C_mac is the moment coefficient around the aerodynamic centre
- C_m is the moment coefficient given (0.02)
- l_cg is the distance from the centre of gravity to the aerodynamic centre (0.05c)
- MAC is the Mean Aerodynamic Chord of the wing

However, the equation requires the Mean Aerodynamic Chord (MAC) of the wing. Since this information is not provided, we cannot directly calculate the moment coefficient around the aerodynamic centre.