Consider a Mach 2 airstream at standard sea-level conditions. Calculate the total pressure of this flow.

Consider a Mach 2 airstream at standard sea-level conditions. Calculate the total pressure of this flow. Compare this result with (a) the stagnation pressure that would exist at the nose of a blunt body in the flow and (b) the erroneous result given by Bernoulli’s equation, which of course does not apply here.

 


 

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