Consider a jet-propelled airplane with the following parameters: weight W = 110 kN wing area S = 50 m wing span b = 22 m zero-lift drag coefficient CD0 = 0.02 Oswald efficiency factor e = 0.82 maximum lift coefficient CLmar = 1.5 thrust available at sea-level TA0 = 26 kN air density at sea-level po = 1.225 kg/m The airplane is performing a straight and unaccelerated climb at sea-level. The climb angle is y = 9 degrees and the pilot is applying full thrust available. Calculate the associated rate of climb of the airplane. Enter your answer in metres per second (m/s) in the text box and upload your workings together with those of Question 2 as described in the instructions above