1. An airplane is flying at a velocity of 130 mi1h at a standard altitude of 5000 ft. At a point on the wing, the pressure is 1750.0 /ft2. Calculate the velocity at that point, assuming incompressible flow. 2. Imagine that you have designed a low-speed airplane with a maximum velocity at sea level of 90 . For your airspeed instrument, you plan to use a tube with a 1.3 : 1 area ratio. Inside the cockpit is an airspeed indicator-a dial that is connected to a pressure gauge sensing the tube pressure difference p 1 – P2 and properly calibrated in terms of velocity.

1. An airplane is flying at a velocity of 130 mi1h at a standard altitude of 5000 ft. At a point on the wing, the pressure is 1750.0 /ft2. Calculate the velocity at that point, assuming incompressible flow. 2. Imagine that you have designed a low-speed airplane with a maximum velocity at sea level of 90 . For your airspeed instrument, you plan to use a tube with a 1.3 : 1 area ratio. Inside the cockpit is an airspeed indicator-a dial that is connected to a pressure gauge sensing the tube pressure difference p 1 – P2 and properly calibrated in terms of velocity. What is the maximum pressure difference you would expect the gauge to experience?

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