Aerospace Engineering > GATE 2019 > Normal Shock
The static pressure ratio across a stationary normal shock is given by
where M1 is the upstream Mach number. For a stationary normal shock in air (γ = 1.4, R = 287 J/kg-K) with upstream flow conditions given by: speed 800 m/s, static temperature 300 K and static pressure 1 atm., the static pressure downstream of the shock is _______ atm (round off to 2 decimal places).
Correct : 5.95 to 6.10
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