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The pressure rise from free stream to the nose of the fuselage section of an aircraft is measured in a wind tunnel at 20 degrees
The pressure rise from free stream to the nose of the fuselage section of an aircraft is measured in a wind tunnel at 20 degrees Celsius to be 34 KPa with a wind tunnel air a speed of 900 km/hr. If the test is to simulate flight at an elevation of 12km, what is the prototype velocity and the expected nose pressure rise?
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