Discussion
Arrange these contributions to the yawing moment derivative in the order they are summed:
1. The fuselage, generally destabilising
2. Any propeller ahead of the centre of gravity, destabilising
3. The wing, contributing modestly if swept
4. The fin, strongly stabilising
5. The total, which must be positive for stability
Select the correct sequence.
Answer: A
Correct answer: 1, 2, 3, 4, 5
The order runs through the airframe from nose to tail, ending with the sum. The fuselage comes first, its side area largely ahead of the centre of gravity and therefore destabilising. A tractor propeller is destabilising for the same geometric reason, its side force acting at the disc.
The wing contributes modestly, usefully so if swept, through the drag differential between forward and rear panels. The fin comes last and is by far the largest term, sized precisely to overcome everything before it. The total \( C_{n\beta} \) must be positive for stability, which is what the whole exercise is for.
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