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_m=0.02, determine the moment coefficient of the moment around the aerodynamic centre.

Answer 1

To find the moment coefficient (C_m) around the aerodynamic centre, we can use the following formula:

C_m = (l(cg) / c) * C_L

Given:
l(cg) = 0.05c (distance from the centre of gravity to the wing's aerodynamic centre)
C_L = 0.8 (lift coefficient)

Substituting the given values into the formula, we have:

C_m = (0.05c / c) * 0.8

C_m = 0.05 * 0.8

C_m = 0.04

Therefore, the moment coefficient (C_m) around the aerodynamic centre is 0.04.