In Matlab or python please

Drag and Thrust (x 1000 lb) Consider the T-38 aircraft J85-GE5A engine data Aircraft weight is 10,000lbf and flight altitude is 10,000ft. Reference area is 170ft2. Note the T38 has two engines. a) Plot the ratio of max thrust with afterburner on ("Max") to max thrust with afterburner off ("Mil") TMax/TMil vs. Mach number M for 0.2M1 using 0.05 Mach number increments. b) If the aircraft is flying horizontally in a steady condition at M=0.6 with thrust T equal to TMil, compute the drag D in lbf, drag coefficient CD, and velocity V in ft/s. c) Starting from the steady state condition in b), if the aircraft thrust is instantaneously changed to T=TMax, compute the initial aircraft acceleration V in ft/s2. d) As the aircraft flys under the condition in c), drag will increase and acceleration will decrease eventually to zero. Compute the final velocity in ft/s. e) Compute the time to reach this final velocity assuming an average acceleration value equal to one-half of the value from c)