I need to compute the range and endurance of a small airplane applying the Breguet equations:
$R = \frac{\eta_{p, cruise}}{C_{bhp, cruise}} \frac{L}{D}_{cruise} \ln{\frac{W_1}{W_2}}$
$E = \frac{\eta_{p, loiter}}{C_{bhp, loiter}} \sqrt{2\rho S_{\infty}} \left(\frac{C_L^3/2}{C_D}\right)_{loiter} \left(W_2^{-1/2} - W_1^{-1/2}\right)$
Use propeller efficiency = 0.7, W1 = 96 kg, W2 = 80 kg, rho =1.112 kg/m³, SFCB = 413 g/kw-hr
The Cl and Cd coefficient of the wing are presented in the following table. The additional
drag of the airplane needs to be calculated analytically (provide sources). Below is a picture with
the general dimensions of the airplane in meters.
\begin{tabular}{|c|c|c|c|c|c|}
\hline
Configuration & $(C_L)_{loiter}$ & $(C_D)_{loiter}$ & $(\frac{L}{D})_{cruise}$ & S $(m^2)$ & Range (km) & Endurance (hours) \\
\hline
1 & 1.01055 & 0.03881 & 27.5 & 3.358 & ? & ? \\
2 & 0.989877 & 0.04358 & 24 & 3.1 & ? & ? \\
\hline
\end{tabular}