For the wing foil, dtermine the aerodynamic lift. density
ofair=1.21 kg/m3. area= 200m2.
speed=150m/s, speed=100m/s.

The lift is the force generated on a body that travels through a fluid, perpendicular to the speed of the incident current. The mathematical model is given as

Here,

= Density

A = Cross sectional Area

=  Upper Velocity

= Down Velocity

Our values are given as

=1.21 kg/m3.

A= 200m2.

=150m/s

=100m/s

Replacing we have,

Therefore the areodynamic lift would be

dicrrdirrkdirckrrdrrk ; jhgfdsgrthyjkul; i'lkjhgfdskhjl; jhgdfs

acceleration = (change in speed) / (time for the change)

change in speed = (20-120)= -100 m/s.

1.5 min = 90 sec

acceleration = -100/90 = -1.11 m/s^2.

we don't care about the 150kg or the 2,500 meters. they don't make any difference.

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