Discussion
A wing contributes \( +0.10 \) to the moment slope, the fuselage \( +0.04 \) and the tail \( -0.22 \). The total slope is
Answer: A
Correct answer: Minus 0.08, so the aeroplane is stable
The contributions add directly:
\[ \frac{\mathrm{d}C_m}{\mathrm{d}C_L} = +0.10 + 0.04 - 0.22 = -0.08 \]A negative slope means that an increase in lift coefficient produces a nose-down moment, which reduces the incidence that caused it, so the aeroplane is statically stable. The magnitude, 0.08, is the static margin in chords. Note how much of the tail\'s 0.22 is consumed simply in cancelling the wing and fuselage.
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