Discussion
For a normal shock at \( M_1 = 2 \), the static temperature ratio \( T_2/T_1 \) is nearest to
Answer: A
The equation of state gives the temperature ratio as the pressure ratio divided by the density ratio, so \( 4.5 / 2.667 = 1.688 \). A stream at 250 K would emerge at about 422 K, which is why shock heating matters structurally even at modest supersonic speeds.
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