We need to determine several properties of the flow.
Given data:
Reservoir temperature, $T_0 = 600 \text{ K}$
Throat area, $A^* = 2 \text{ cm}^2 = 2 \times 10^{-4} \text{ m}^2$
Area where normal shock forms, $A_x = 6 \text{ cm}^2 = 6 \times 10^{-4} \text{
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