Question

For the wing foil, dtermine the aerodynamic lift. Density

ofair=1.21 kg/m3. Area= 200m2.
Speed=150m/s,speed=100m/s.

Answer 1

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

`F_L = (1)/(2) \rho A (V_t^2-V_u^2)`

Here,

`\rho`= Density

A = Cross sectional Area

`V_2` = Upper Velocity

`V_1` = Down Velocity

Our values are given as

`\rho` =1.21 kg/m3.

A= 200m2.

`V_2`=150m/s

`V_1`=100m/s

Replacing we have,

`F_L = (1)/(2) \rho A (V_t^2-V_u^2)`

`F_L = (1)/(2) (1.21) (200) ((150)^2-(100)^2)`

`F_L = 1512500N`

Therefore the areodynamic lift would be
`1.512*10^6N`