Correct option is (a) 9071.07
Best explanation: Given, a civil aircraft.
Lift off speed V1 = 80m/s, maximum lift coefficient CL=2.8.
Wing loading is given by,
W/S = 0.5*ρ*V^2*CL
Where, V = V1/1.1 = 80/1.1=72.72m/s
Hence, wing loading is given by,
W/S = 0.5*ρ*V^2*CL
W/S = 0.5*1.225*72.72^2*2.8 = 9071.07.