Question

For the wing foil, dtermine the aerodynamic lift. Density

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

$F_L = \frac{1}{2} \rho A (V_t^2-V_u^2)$

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,

$F_L = \frac{1}{2} \rho A (V_t^2-V_u^2)$

$F_L = \frac{1}{2} (1.21) (200) ((150)^2-(100)^2)$

$F_L = 1512500N$

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