on MATLAB please

The 1959 ARDC Model Atmosphere has the following properties: Sea level temperature 288.16 K Sea level pressure 101.325 kPa Sea level density 1.2250 kg/m^3 Gradient layer 1 -6.5*10-3 Km up to 11km Isothermal layer 1 11000-25000 m Gradient layer 2 3 10-3 K/m up to 47km Isothermal layer 2 47000-53000 m Gradient layer 3-4.5*10-3 K/m up to 79km Isothermal layer 3 79000-90000 m Gradient layer 4 4.0*10-3 K/m up to 100km A) Draw by hand a sketch of the atmosphere. Include: pressure, temperature, and density variations with height up to 100km, and annotate the approximate height of a tall mountain and the cruise altitude of a commercial airliner. B) Use equations for the standard atmosphere derived in class to calculate temperature, density, and pressure at the following altitudes. Do these calculations by hand and show your work 4,500 ft 32,000 ft 42,000 ft 82,000 ft C) Write a MATLAB script to call a function which will calculate the air properties at a given altitude using the 1959 ARDC standard atmosphere model above. Comment all major lines of code (creating and setting variables, with units; calling the function). The function should not output any variables to the command window, all outputs should come from the scrip m-file (suppress with semi-colon). The function should have the first line: function IT, P, rho] = name(h); D) Test your program at the altitudes listed above. Place the results from your hand calculations and your MATLAB code into a table for comparison. Compare the results to the results from an external reference. Comment on any differences/similarities you notice. E) Create plots depicting the properties of the standard atmosphere up to 100km. Plot temperature, pressure, and density on a subplot with height as the y-axis