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
Step-by-step 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:
![C_(L) =2\pi sin\theta](https://img.qammunity.org/2021/formulas/engineering/college/oi95f2bjv6hw1qypcwlmtae34tpirvv1cb.png)
Here, θ=90°, thus, the expression is:
![C_(L) =2\pi](https://img.qammunity.org/2021/formulas/engineering/college/b3l0i5k5g9miipg4ovzdns3wbhfnl5uflf.png)
The mathematical expression to calculate the aerodynamic force is:
![F_(L) =(1)/(2) C_(L) \rho Av^(2) =\pi *\rho *A*v^(2) =\pi *1.1649*7.4*20^(2) =1.083x10^(4) N](https://img.qammunity.org/2021/formulas/engineering/college/xair11y4jaiwjmguucdwtk2ubh9rqb6kqf.png)
b) If the CL factor changes, the response also changes, since the aerodynamic force is dependent on said factor