The static pressure ratio across a stationary normal shock is given by $ \frac{p_{2}}{p_{1}}=1+\frac{2 \gamma}{\gamma+1}\left(M_{1}^{2}-1\right) $ where $M_{1}$ is the upstream Mach number. For a stationary normal shock in air $(\gamma=1.4, R=$ $287 \mathrm{~J} / \mathrm{kg}-\mathrm{K})$ with upstream flow conditions given by: speed $800 \mathrm{~m} / \mathrm{s}$, static temperature $300 \mathrm{~K}$ and static pressure 1 atm., the static pressure downstream of the shock is ______________atm. (round off to 2 decimal places).

The static pressure ratio across a stationary normal shock is given by $ \frac{p_{2}}{p_{1}}=1+\frac{2 \gamma}{\gamma+1}\left(M_{1}^{2}-1\right) $ where $M_{1}$ is the upstream Mach number. For a stationary normal shock in air $(\gamma=1.4, R=$ $287 \mathrm{~J} / \mathrm{kg}-\mathrm{K})$ with upstream flow conditions given by: speed $800 \mathrm{~m} / \mathrm{s}$, static temperature $300 \mathrm{~K}$ and static pressure 1 atm., the static pressure downstream of the shock is ______________atm. (round off to 2 decimal places).

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