Discussion
A fin contributes \( +0.14 \) to the yawing moment derivative and the fuselage \( -0.05 \). The total derivative is
Answer: B
Correct answer: Plus 0.09, and therefore stable
Contributions to the yawing moment derivative simply add:
\[ C_{n\beta} = +0.14 - 0.05 = +0.09 \]
A positive \( C_{n\beta} \) means a sideslip to the right produces a nose-right yawing moment, turning the aeroplane back into the relative wind - so the aeroplane is directionally stable. The arithmetic also shows the fin doing exactly its job: the fuselage alone is destabilising at \( -0.05 \), and the fin's \( +0.14 \) more than cancels it. That surplus is the stability margin the designer is buying.
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