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The weather conditions affect pressure, altitude and density of air 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 a pressure to 22,632 Pa as well as for the density of air using Equation 2.2 -RLD Equation 2.1 h= b + LD PM pa RT) Equation 2.2 where, Po = static pressure at sea level, 101,325 Pa To - standard temperature at sea level, 288 K L = standard temperature lapse rate = -0.0065 K/m h = height about sea level, m hp-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 22,632 to 2,485 Pa), have a constant temperature throughout the layer. This requires different equations to determine the altitude for a given pressure. Equations 2.3 and 2.4 specify the calculation for altitude and density of air respectfully in this zero temperature lapse rate layer. h = hp + -OM P= Po explore my Ch ho)] Equation 2.3 Equation 2.4 For Equations 2.3 and 2.4 where hy = 11 km, Po = 22,632 Pa, po = 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 altitude and density of air at troposphere or stratosphere and display an error message if other option is inserted. Expected output should be altitude and density of air at every decrement of 1000 Pa as shown in Figure 2.1. Write your answer in the box given in Figure 2.2. X Editor - /Users/agusarsad/Documen.. TEST22.m Altitute.txt 1 Pressure Altitute Density 2 (Pa) (m) (kg/m3) 3 101325 1.2256 4 1e8325 84 1.2135 5 99325 168 1.2014 6 98325 253 1.1893 7 97325 338 1.1773 OWN Editor-/Users/agusarsad/Docume... O TEST22.m Altitute.txt + 1 Pressure Altitute Density (Pa) (m) (kg/m3) 22632 11000 0.3648 21632 11286 0.3487 29632 11586 8.3326 19632 11901 0.3164 18632 12232 0.3003 air at every decrement of 1000 Pa as shown in Figure 2.1. Write your answer in the box given in Figure 2.2. Editor - /Users/agusarsad/Documen... TEST22.m Altitute.txt"> 1 Pressure Altitute Density 2 (Pa) (kg/m3) 3 101325 @ 1.2256 4 100325 84 1.2135 5 99325 168 1.2014 6 98325 253 1.1893 7 97325 338 1.1773 8 96325 425 1.1652 9 95325 512 1.1531 10 94325 599 1.1410 11 93325 688 1.12891 12 13 14 15 78325 2118 0.9474 16 77325 2221 0.9353 17 76325 2325 8.9232 18 19 20 21 50325 5524 0.6087 22 49325 5672 8.5966 23 48325 5822 8.5845 24 25 26 27 30325 9087 0.3668 28 29325 9311 0.3547 29 28325 9541 8.3426 30 27325 9778 0.3385 31 26325 10022 2.3184 32 25325 10274 @.3063 33 24325 10534 0.2942 34 23325 10803 0.2821 35 Editor - /Users/agusarsad/Docume... +1 TEST22.m Altitute.txt 1 Pressure Altitute Density 2 (Pa) (kg/m3) 3 22632 11000 0.3648 4 21632 11286 0.3487 5 20632 11586 0.3326 6 19632 11901 0.3164 7 18632 12232 0.3003 B 17632 12582 0.2842 9 16632 12952 0.2681 10 15632 13345 0.2520 11 14632 13764 0.2358 12 13632 14213 0.2197 13 12632 14695 0.2836 14 11632 15218 0.1875 15 10632 15788 0.1714 16 9632 16414 0.1553 17 8632 17108 0.1391 18 7632 17889 0.1230 19 6632 18779 e. 1969 20 5632 19814 .0908 21 4632 21053 0.0747 22 3632 22594 0.0585 23 2632 24635 0.0424 24 . 1 Clc 2 Clear 3 4 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 Figure 2.2: Answer of MATLAB program