Discussion
A flow at \( M = 2 \) has a static temperature of \( 300 \) K. Its stagnation temperature, with \( \gamma = 1.4 \), is
Answer: B
The relation is \( T_0 / T = 1 + 0.2 M^2 \) for air. Here \( 1 + 0.2 \times 4 = 1.8 \), so \( T_0 = 300 \times 1.8 = 540 \) K. The large rise shows why kinetic heating becomes a structural problem at supersonic speed even before hypersonic conditions are reached.
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