4. When a Pitot tube is placed in a supersonic flow there is a normal shock wave immediately upstream of the probe. A Pitot tube on a supersonic aircraft senses a stagnation pressure $p_0 = 200$ kPa and a static pressure $p = 160$ kPa downstream of the shock wave. The stagnation temperature is 400 K. Consider the following: i) Determine the Mach number upstream of the shock wave. ii) Calculate the aircraft velocity (m/s).

          4.
When a Pitot tube is placed in a supersonic flow there is a normal shock wave
immediately upstream of the probe. A Pitot tube on a supersonic aircraft senses a
stagnation pressure $p_0 = 200$ kPa and a static pressure $p = 160$ kPa downstream of
the shock wave. The stagnation temperature is 400 K. Consider the following:
i)
Determine the Mach number upstream of the shock wave.
ii) Calculate the aircraft velocity (m/s).

4.
When a Pitot tube is placed in a supersonic flow there is a normal shock wave
immediately upstream of the probe. A Pitot tube on a supersonic aircraft senses a
stagnation pressure p0 = 200 kPa and a static pressure p = 160 kPa downstream of
the shock wave. The stagnation temperature is 400 K. Consider the following:
i)
Determine the Mach number upstream of the shock wave.
ii) Calculate the aircraft velocity (m/s).

Added by Jose Manuel G.

University Physics with Modern Physics

Hugh D. Young 14th Edition

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Solved by Expert Sikandar Baig

Step 1

This relationship is given by: pâ‚€ / p = (1 + ((Î³ - 1) / 2) * Mâ‚€²^2)^(Î³ / (Î³ - 1)) where pâ‚€ is the stagnation pressure, p is the static pressure, Î³ is the specific heat ratio (which is approximately 1.4 for air), and Mâ‚€′ is the Mach number upstream of Show more…

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When a Pitot tube is placed in a supersonic flow, there is a normal shock wave immediately upstream of the probe. A Pitot tube on a supersonic aircraft senses a stagnation pressure pâ‚€ = 200 kPa and a static pressure p = 160 kPa downstream of the shock wave. The stagnation temperature is 400 K. Consider the following: i) Determine the Mach number upstream of the shock wave. ii) Calculate the aircraft velocity (m/s).