I need a MATLAB Code for this. I cant get a code that actually run! Please help

The pressure and temperature of the atmosphere change constantly based on a number of factors including altitude, latitude/longitude, time of day, and season. To take all these varlations into account when considering the design and performance of flight vehicles is impractical. Therefore, a standard atmosphere is frequently used to provlde engineers and scientists with a common reference for their research and development. The International Standard Atmosphere is one such model of how conditions of the earth's atmosphere change over a wide range of altitudes or elevations. The following table shows the values of temperature and pressure at selected altitudes. Layer Index,Layer Name Base Geopotential se Rate Bese T perature ) | Base Pressure,IP Altitude Above MSL, Base Temperature T(C) (C/km) (Pa) 101325 22632 5474.9 868.02 10.91 66.939 3.9564 0.3734 (km) 0 -6.5 0 Troposphere Troposphere Stratosphere Stratosphere Stratosphere Mesosphere Mesosphere Mesospause 20 32 47 51 71 84.852 15 -56.5 56.5 -44.5 -2.5 -2.5 -58.5 -86.28 2.8 0 -2.8 -2.0 6 The temperature at each altitude can then be computed as where TV temperature at altitude hrq, 7-the base temperature for layer ,CC), Y,-lapse rate or the rate at which atmospheric temperature decreases linearly with Increase in altitude for layer I('C/km), and hi base geopotential altitude above mean sea level (MSL) for layer i The pressure at each altitude can then be computed as p(h)-Pi+( i) h- h where pt)- pressure at altitude h (Pa N/m2) and pi the base pressure for layer (Pa). The density. p be calculated according to a molar form of the ideal gas law (kg/m3), can then pM where M# molar mass ( 0.0289644 kg/mo), R the universal gas constant (8.3144621 J/(mol-K), and ra-absolute temperature (K) T 273.15 Consider the figure below. 20 kips/ft 150 kip-ft 15 kips 5 Consider the following script: % Script to generate a plot of temperature, pressure and density % for the International Standard Atmosphere clc,clf h [e 11 20 32 47 51 71 84.852] gamma = [-6.5 0 1 2.8 e-2.8-2); T = [15-56.5-56.5-44 , 5-2.5-2.5-58.5-86.28); p [101325 22632 5474.9 868.02 110.91 66.939 3.9564 0.3734]; hint [0:0.1:84.852]; for i 1:length(hint) [Tint(i),pint (i),rint (i)] StdAtm(h, T,p, gamma,hint (i)); end % Create plot % Function call to test error trap [Tint ( ), pint (i ), rint(1)]sStdAtn(h,T,p,gamma , 85); Use the given script as the starting point to create a 3-panel plot of altitude versus the properties as depicted in the given figure (Please upload your response/solution using the controls below)