Acan you help to design this program
The weather conditions affect pressure and altitude calculations, the pressure and temperature at sea level must be known. First layer of atmosphere (troposphere), the altitude at a given air pressure can be calculated using Equation 2.1 for an altitude up to 11 km. The equation can also be arranged to calculate the density of air using Equation 2.2 -AM RL) P=P P,[1 + (h ht) Equation 2.1 PM P= RT Equation 2.2 where, Po-static pressure at sea level, 101,325 Pa Ti - standard temperature at sea level, 288 K Lo standard temperature lapse rate = -0.0065 K/m h = height (altitude) about sea level, m hy = height at the bottom of atmospheric layer, m R-universal gas constant -8.31432 Nm/kmol.K g-gravitational acceleration constant -9.80665 m/s2 M-molar mass of Earth's air -0.0289644 g/kmol Stratosphere layer is the second layer of atmosphere (from 11km to 20km), have a constant temperature throughout the layer. This requires different equations to determine the pressure. Equation 2.3 specify the calculation for pressure respectfully in this zero temperature lapse rate layer. New density of air also affected by the pressure and can be calculated by the Equation 2.4 P= P, exp [-gh-R) - 1] R.T Equation 2.3 + p= P exp PC-en (n ho))] Equation 2.4 For equations 2.3 and 2.4 where hy = 11 km, Po=22,632 Pa, P = 0.3648 and T, correspond to the altitude, pressure, density and temperature at the bottom of the stratosphere. The temperature at the bottom of the stratosphere is determined by subtracting 71.5 K from the temperature at sea level. Design a MATLAB programming using a decisional structure Switch-Case approach to calculate the atmosphere pressure and density of air at troposphere or stratosphere at every 1 km distance and display an error message if other option is inserted. Expected output should be pressure and density of air at every 1 km as shown in Figure 2.1. Write your answer in the box given in Figure 2.2. Editor - /Users/agusarsad/D... TEST21.m x Altitute.txt x + 1 Altitude Pressure Density 2 (m) (Pa) (kg/m3) 3 101325 1.2256 4 1000 89869 1.0871 5 2000 79485 0.9615 6 3000 70095 0.8479 7 4000 61624 0.7454 8 5000 54001 0.6532 9 6000 47161 0.5705 10 7000 41040 0.4964 11 8000 35578 0.4304 12 9000 30721 0.3716 13 10000 26415 0.3195 14 11000 22612 0.2735 151 Editor - /Users/agusarsad/Do... TEST21.m x Altitute.txt x + 1 Altitude Pressure Density 2 (Pa) (kg/m3) 3 11000 22632 0.3648 4 12000 19328 0.3115 5 13000 16507 0.2661 6 14000 14097 0.2272 7 15000 12039 0.1941 8 16000 10282 0.1657 9 17000 8781 0.1415 10 18000 7499 0.1209 11 19000 6404 0.1032 12 20000 0.0882 13 | 5469 (a) Troposphere (b) Stratosphere Figure 2.1 : Expected output of MATLAB programming
