Answer:
a) the aerodynamic force is 1.083x10⁴N
b) If the CL factor changes, the response also changes, since the aerodynamic force is dependent on said factor
Explanation:
Given data:
v=20m/s
Apole=20*0.12=2.4m²
Aflag=2*2.5=5m²
The total area is:
Atotal=2.4+5=7.4m²
The properties of the air at 30°C are:
v=1.6036x10⁻⁵m²/s
ρ=1.1649kg/m³
a) First, we need to calculate the coefficient of lift:
[tex]C_{L} =2\pi sin\theta[/tex]
Here, θ=90°, thus, the expression is:
[tex]C_{L} =2\pi[/tex]
The mathematical expression to calculate the aerodynamic force is:
[tex]F_{L} =\frac{1}{2} C_{L} \rho Av^{2} =\pi *\rho *A*v^{2} =\pi *1.1649*7.4*20^{2} =1.083x10^{4} N[/tex]
b) If the CL factor changes, the response also changes, since the aerodynamic force is dependent on said factor