Aerospace Engineering > GATE 2012 > Airfoil Theory
An airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively (specific gas constant is 287 J/kg-K). the circulation on the airfoil in m2/s is
Correct : 0.540 to 0.560
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