Mean Aerodynamic Chord Calculation
2 0
A1 A 2
38 38
Y
2 y X 18 5
2 4 33 2 S [ X 18]dx [ X ]dx [ X 4]dx 5 16 2 19 0 10 0
10
1 2 33 1 38 S [ X 2 18X C1 ]10 [ X 2 X C2 ]10 [ X 2 4 X C3 ]38 0 0 5 16 2 19
y
1 0
4 33 X 16 2
A1
y 2 X 4 19
M A C
A2
X
0 0 1 0 1 7 2 0 3 0 4 0
100 2 33 2 33 1 S 180 C1 C1 (38 2 (38 C2 (10 2 (10 C2 (38 2 4(38 C3 C3 ) ) ) ) ) ) 5 16 2 16 2 19
S 160 180 .5 627 12 .5 165 76 152 378 ft 2
MAC Area 378 9.95 ft span 38
y upper y lower [
4 33 2 X ] [ X 4] 9.95 16 2 19
0.25 X 0 .10 X 16.5 4 9.95 0.15 X 2.55 X 17 ft
To find LEMAC (Leading edge of the Mean Aerodynamic Chord)
y
4 33 (17 ) 12 .25 16 2
To find TEMAC (Trailing edge of the Mean Aerodynamic Chord) MAC = 12.25' - 2.21' = 10.04'
y
2 (17) 4 2.21 19
The Mean Aerodynamic Chord is the chord line drawn parallel to the longitudinal axis which passes through the geometric center (centroid) of the area of the wing planform. It is related to stability and control characteristics of swept wing aircraft.