Problem $1$:

A turbofan engine having by pass ratio of $10$ is fitted to an aircraft flying at a speed of $870k\frac{m}{h}r$ with atmospheric $($static$)$ temperature and pressure of $-48C$ and $29$ kPa $,$ respectively. The engine has the following component performance:

$\backslash$table$[[,$Efficiency,Rp$,$Cp$,$