Estimate the stagnation pressure sensed by the pitot tube.

A supersonic aircraft cruises at M = 2.2 at 12 km altitude. A pitot tube is used to sense pressure for calculating air speed. A normal shock stands in front of the tube. Evaluate the local isentropic stagnation conditions in front of the shock. Estimate the stagnation pressure sensed by the pitot tube. Show static and stagnation state points and the process path on a T s diagram.