This is Bernoulli's principle problem (you need to assume laminar flow; otherwise the calculation is near impossible). Bernoulli's principle says,
(1/2)*density*(flow velocity)^2 + density*g*height + Pressure = constant.
Between the top of the wing and the bottom, the height difference should be small enough that we can ignore it. Then, we have (rho = density, v = flow velocity, and P = pressure)
(1/2)*rho*v^2 + P = constant.
When the air gets cut through by the airplane wing, although their flow velocity changes, we have no reason to think that the constant on the right hand side (which is related to energy conservation, by the way) will change. So, that must mean that the pressure should change to compensate for the change in velocity, so that the constant remains, well constant. Putting this into equation, we have,
(1/2)*rho*v_below^2 + P_below = (1/2)*rho*v_above^2 + P_above.
P_above. - P_below = 1/2 *rho*(v_below^2 - v_above^2 )
P_above. - P_below = 1/2 *1.2(60^2 - 70^2) = ) = 0.6*(3600-4900) = -780 N/m^2
or we can say P_net = 780 N/m^2
We know everything necessary to calculate P_above - P_below. Once we have that, then we use the fact that
F_net = area*P_net, = 16.2*780 = 12636 N
Thanks & Regards,
Nirmal Singh
Askiitians Faculty