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What will be the weight fraction of the aircraft at final mission segment w.r.t. W0?

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What will be the weight fraction of the aircraft at final mission segment w.r.t. W0?

(a) Multiplication of individual weight fraction

(b) Division of individual weight fraction

(c) Addition of individual weight fraction

(d) Subtraction of individual weight fraction

This question was posed to me in an interview.

The origin of the question is Conceptual Sketch Sizing in division Conceptual Sketch Sizing of Aircraft Design

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The correct option is (a) Multiplication of individual weight fraction

The best I can explain: We can divide whole mission profile of aircraft into number of mission phases or legs. Fuel fraction at each mission segment will be fuel weight at end of phase to that of beginning. Hence, if there are z – number of mission phase then, final mission phase fraction will be multiplication of individual weight fraction which will give weight fraction w.r.t. take-off gross weight W0

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