Can you guys help me trying to figure this out and with the plot as well? Thanks!
The following data of the bypass ratios α = 1, α = 3, and α = 10 are being considered for an
ideal turbofan operating at an altitude of 10 km. For each bypass ratio, using MATLAB or
Python, plot the specific thrust ratio (F R), the Thrust specific fuel consumption (S), and overall
efficiency (ηO) versus the free stream Mach number M0 in a range from 0 to 3.0. Consider the
following design parameters: Fan pressure ratio: πF=2, compressor pressure ratio: πc=20, fuel
heating energy: hP R=43.5 MJ/Kg, and exit temperature of the combustor: Tt4=1420