Stagnation pressure across a normal shock wave

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A body is reentering the earth's atmosphere at a Mach number of 20. In front of the body is a shock
wave. Opposite the nose of the body, the shock can be seen to be normal to the flow direction. Determine the stagnation pressure and temperature to which the nose is subjected. Assume that the air behaves as a perfect gas (neglect dissociation) with constant γ = 1.4. The ambient pressure and temperature are equal to 1.0 kPa and 220 K.

I know all the relevant equations. My question is what is meant by ambient temperature. Does it mean static or stagnation pressure of the free stream?
 

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