To find the static margin of this A340-600 aircraft, we need to first calculate the neutral point location. The neutral point is the aerodynamic center of the aircraft, where the pitching moment does not change with changes in angle of attack.
The neutral point (NP) is given by the formula:
NP = CG - (C_Mα / C_Lα) * MAC
Where:
CG = center of gravity location, which is 39.2 m from the nose
C_Mα = Change in pitching moment coefficient with respect to the change in angle of attack
C_Lα = Change in lift coefficient with respect to the change in angle of attack
MAC = Mean Aerodynamic Chord
To calculate the neutral point, we need to find the values of C_Mα, C_Lα, and MAC.
C_Mα can be approximated as the sum of the wing and tail contributions:
C_Mα = C_Mα_wing + C_Mα_tail
C_Mα_wing = - (a * S_H * l(wing)) / S
C_Mα_tail = - (a_t * S * C_) / S
C_Lα can be approximated as the lift curve slope of the wing:
C_Lα = 2 * π * a * (S / S)
Since the value of MAC is not given, we assume that MAC is equal to the wing length (l(wing)).
Now we can substitute these values into the formula to find the neutral point (NP):
C_Mα_wing = - (4.8 / rad * 93 m^2 * 34.9 m) / 437 m^2 = -0.3167
C_Mα_tail = - (5.2 / rad * 437 m^2 * 8.25 m) / 437 m^2 = -1.0357
C_Lα = 2 * π * 4.8 / rad = 30.1441
NP = 39.2 m - (-0.3167 / 30.1441) * 34.9 m = 6.5396 m
The static margin is the distance between the neutral point and the center of gravity, so the static margin is:
Static margin = CG - NP = 39.2 m - 6.5396 m = 32.6604 m
Therefore, the static margin of this A340-600 aircraft is 32.6604 meters.
For this aircraft, you are given the following parameters: l(wing)=34.9m, l(tail)-67.8m, S=437 m^2, S_H=93 m^2, C_=8.25m, a=4.8/rad , a_t=5.2/rad. Furthermore we will assume that the downwash angle is equal to 10% of the angle of attack of the wing. Given that the centre of gravity of this A340-600 is situated 39.2 metres from the nose, find the static margin (in metres) of this A340.
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