Deploying trailing-edge flaps on an aircraft wing primarily:

(A) Increases section camber, shifting the zero-lift line and increasing maximum lift coefficient C_{L,max}

(B) Eliminates boundary layer friction completely

(C) Increases wing aspect ratio

(D) Prevents supersonic shock formation at Mach 3

Answer Key:

A

### Solution: Trailing-edge flaps effectively increase wing section camber, shifting lpha_{L=0} more negative and shifting the C_L vs lpha curve upward to increase C_{L,max}. Correct: A.

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