MATLAB help please!!

Below is the link that was provided to me to use the standard atmosphere function. I computed everything by hand but I am having troubling figuring out how to use the MATLAB function to obtain the outputs and plot the thrust against the altitude.

https://www.mathworks.com/matlabcentral/fileexchange/28135-standard-atmosphere-functions

= = - Compute and plot the thrust of a rocket engine for constant exhaust conditions, Pe = 1.00 kg/m, pe 0.030 MPa, ue 1500 m/s, and exit area Ae = 1.0 m, as a function of altitude from sea level to 25 km altitude. (Note: use the standard atmosphere for ambient pressure as a function of altitude; Use the MATLAB function