Please use MATLAB and proper comments

Many different quantities in aerospace engineering depend on the temperature, pressure, and density of the atmosphere at the current altitude. The atmosphere can be modeled as a series of alternating isothermal and gradient regions. Within the isothermal region, the pressure (p) and density (p) are defined by the following equations 2. e-lo/(RT)](h-h1) P1 where R is the specific gas constant of 1716 (ft-lbf)/(slug-R), go is the acceleration due to gravity of 32.2 ft/s2, T represents the constant temperature in the isothermal layer in R, and h represents the geopotential altitude in ft. The subscript 1 indicates that the value of the parameter is from the base (i.e., the beginning) of the region. The first isothermal region in the atmosphere begins at approximately 36089 ft, where T 389.99 R, p 474.11 lbf/ft2, and p - 0.0007074 slug/ft3, and ends around 82021 ft in altitude. Write a program that will Ask the user for the geopotential altitude, and the base values for altitude, temperature, pressure, and density for the current isothermal region Calculate the pressure, density at the specified altitude. (Note: Write this task as a function.) a. b. c. Display the results to the command windovw One example of running this program is as follows (user input is highlighted in yellow) Enter the current altitude (ft): 47000 Enter the base altitude for the region (ft): 36089 Enter the base temperature (deg Rankine): 389.99 Enter the base pressure (lb/ft 2) 474.11 Enter the base density (slug/ft^3): 0.0007074 At a geopotential altitude of 47000.00 ft, the pressure is 280.47 lb/ft"2 and the density is 0.00042 slug/ft^3