General Thrust Equation Please Show this being done in MATLAB. Consider a turbojet-powered engine aircraft flying at a v

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General Thrust Equation
Please Show this being done in MATLAB.
Consider a turbojet-powered engine aircraft flying at a velocity
of 200 m/s. The turbojet engine has an inlet area 6.5 m2 .
(1) Calculate and plot the thrust generated (N) by the engine
for an exit area and pressure of 3.6 m2 and 10,600 Pa,
respectively. Use an exhaust gas velocity for the range of 470 to
600 m/s at two different altitude (sea level, and 4,000 m). Use the
corresponding density for each altitude to calculate the air mass
flow rate. Assume exit pressure is constant for both altitudes.
(2) Calculate and plot the thrust generated (N) for a constant
exit velocity of 500 m/s for an exitto-inlet area ratio (Ae/Ai) for
the range of 0.1 to 0.5 at the same two altitudes used before.
Assume inlet area is constant. For this problem, assume 𝑚̇ 𝑎𝑖𝑟 ≈
𝑚̇𝑓𝑢𝑒𝑙. Discussed the results obtained.
PLEASE SHOW THIS IN MATLAB CODE, for this is where I am running
into problems. Thank you soo much!