The $1959$ ARDC Model Atmosphere has the following parameters:

Sea level temperature $288\mathrm{.}16K$

Sea level pressure $101\mathrm{.}325$kPa

Sea level density $1\mathrm{.}2250k\frac{g}{m^{{?}^{{?}^{?}}}}3$

Gradient layer $-0\mathrm{.}0065\frac{K}{m}$ up to $11km$

Isothermal layer $11km$ to $25km$

Gradient layer $0\mathrm{.}0030\frac{K}{m}$ up to $47km$

Isothermal layer $47km$ to $53km$

Gradient layer $-0\mathrm{.}0045\frac{K}{m}$ up to $79km$

Isothermal layer $79km$ to $90km$

Gradient layer $0\mathrm{.}0040\frac{K}{m}$ up to $100km$

Create a sketch $($by hand or any drawing tool$)$ of the atmosphere

pressure, temperature, and density with altitude up to $100km.$ Please

use altitude for the vertical axis; the temperature, pressure, and density

do not have to be to scale.

Annotate the sketch with the approximate height of a tall mountain and

the cruise altitude of a commercial airliner.

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.

$7,500ft$

$33,000ft$

$42,000ft$

$80,000ft$

Write a MATLAB function that calculates the air properties at a given

altitude using the $1959$ ARDC standard atmosphere model. The

function should not output any variables to the Command Window

$($suppress with semi$-$colon$).$