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/ft2 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 both p and a are proportional to T 1/2. Let subscripts 1 and 2 denote the free-flight and wind-tunnel conditions, respectively. For C C2 and Cp1 = Co2, the wind-tunnel flow must be dynamically similar to free flight. So, M, = M2 and Re, = Re,. %3D

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/ft2 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 both p and a are proportional to T 1/2. Let subscripts 1 and 2 denote the free-flight and wind-tunnel conditions, respectively. For C C2 and Cp1 = Co2, the wind-tunnel flow must be dynamically similar to free flight. So, M, = M2 and Re, = Re,. %3D

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.49P

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