Table 7:
Assumptions made for T-Tail.
Assumed values
C
h
0.95% of 0.4 = 0.380
C
v
0.95% of 0.7 = 0.067
AR
v
0.700
AR
h
3.000
L
t
45% × Fuselage Length = 0.122 m
λ
v
0.600
λ
h
0.600