Anormal shock wave takes place during the flow of air at a mach number of 1.8. the static pressure and temperature of the air upstream of the shock wave are 100 kpa (abs.) and 150c. determine the mach number, pressure and temperature downstream of the shock.

The pressure upstream and downstream of a shock wave are related as

where,

= Specific Heat ratio of air

M = Mach number upstream

We know that

Applying values we get

Similarly the temperature downstream is obtained by the relation

Applying values we get

The Mach number downstream is obtained by the relation

answer:

explanation:

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answer:

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