We wish to design a wind tunnel test to accurately measure the lift and drag coefficients that pertain to the Boeing 777 in actual flight at Mach 0.84 at an altitude of 35,000 ft. The wingspan of the Boeing 777 is 199.9 ft. However, to fit in the wind tunnel test section, the wingspan of the wind tunnel model of the Boeing 777 is 6 ft. The pressure of the airstream in the test section of the wind tunnel is 1 atm. Calculate the necessary values of the airstream velocity, temperature, and density in the test section. Assume that the viscosity coefficient varies as the square root of the temperature. Note: The answer to this problem leads to an absurdity. Discuss the nature of this absurdity in relation to the real world of wind tunnel testing.
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