Consider a venturi with a throat to inlet area ratio of 0.8, mounted on the side of an airplane fuselage. The airplane is in flight at standard sea level. If the static pressure at the throat is 2100 lb/ft^2. Calculate the velocity of the airplane. (Standard sea level density, pressure and viscosity are 1.23 kg/m^3 (0.002377 slug/ft^3 ), 1.01 x 10^5 N/m^2 (2116 lb/ft^2 ) and 1.73 x 10^-5 N-s/m^2 (3.737 x 10^-7 lb-s/ft^2 respectively.