A Pitot tube mounted on the wing tip of an airplane flying at an altitude of $3 \mathrm{~km}$ measures a pressure of 0.72 bar, and the outside air temperature is $268.66 \mathrm{~K}$. Take the sea level conditions as, pressure $=1.01$ bar, temperature $=288.16 \mathrm{~K},$ and density $=1.225 \mathrm{~kg} / \mathrm{m}^{3} .$ The acceleration due to gravity is $9.8 \mathrm{~m} / \mathrm{s}^{2}$ and the gas constant is $287 \mathrm{~J} /(\mathrm{kg} \mathrm{K})$. Assuming standard atmosphere, the equivalent airspeed for this airplane is ____________$\mathrm{m} / \mathrm{s}$ ( round off to two decimal place ).

A Pitot tube mounted on the wing tip of an airplane flying at an altitude of $3 \mathrm{~km}$ measures a pressure of 0.72 bar, and the outside air temperature is $268.66 \mathrm{~K}$. Take the sea level conditions as, pressure $=1.01$ bar, temperature $=288.16 \mathrm{~K},$ and density $=1.225 \mathrm{~kg} / \mathrm{m}^{3} .$ The acceleration due to gravity is $9.8 \mathrm{~m} / \mathrm{s}^{2}$ and the gas constant is $287 \mathrm{~J} /(\mathrm{kg} \mathrm{K})$. Assuming standard atmosphere, the equivalent airspeed for this airplane is ____________$\mathrm{m} / \mathrm{s}$ ( round off to two decimal place ).