Consider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft? and 390'R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430°R. Calculate the required velocity and pressure of the test airstream in the wind tunnel such that the lift and drag coefficients measured for the wind-tunnel model are the same as for free flight. Assume that bothu and a are proportional to T1/2.
Consider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the freestream pressure and temperature are 432.6 lb/ft? and 390'R, respectively. A one-fiftieth scale model of the 747 is tested in a wind tunnel where the temperature is 430°R. Calculate the required velocity and pressure of the test airstream in the wind tunnel such that the lift and drag coefficients measured for the wind-tunnel model are the same as for free flight. Assume that bothu and a are proportional to T1/2.
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Transcribed Image Text:Consider a Boeing 747 airliner cruising at a velocity of 550 mi/h at a standard altitude of 38,000 ft, where the
freestream pressure and temperature are 432.6 lb/ft? and 390°R, respectively. A one-fiftieth scale model of the
747 is tested in a wind tunnel where the temperature is 430'R. Calculate the required velocity and pressure of
the test airstream in the wind tunnel such that the lift and drag coefficients measured for the wind-tunnel
model are the same as for free flight. Assume that bothu and a are proportional to T1/2.
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