EASA Principles Of Flight Practice Test

Oblique shock waves: The static temperature behind the shock is higher than in front.

True False Cannot be determined Only true at certain Mach numbers

Correct Answer:

True

Explanation:

In an oblique shock, the airflow is decelerated and compressed, converting kinetic energy into internal energy. Since the flow is adiabatic, the stagnation (total) temperature stays the same across the shock. The normal component of the Mach number drops from before to after the shock, and because T0 = T [1 + (gamma-1)/2 M_n^2], a decrease in M_n behind the shock must be accompanied by an increase in static temperature T. Therefore, the static temperature behind the oblique shock is higher than ahead. This holds for any M1 > 1 with a calorically perfect gas like air, so it’s not indeterminate and not limited to certain Mach numbers.

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