Question

Background: The altitude of an airplane, can be determined by measuring the air pressure at altitude. Pressure and elevation are related by AP = - pg Az equation 1 SISTORY where AP is the change in pressure from the ground to the elevation, g is the local gravity constant of 9.81 m/s2. p is the average air density of 1.15 kg/m (assumed constant for this problem), and Az is the change in elevation in meters. UN 0. The local surface air pressure is 1020 mbar. Determine the elevation of a plane as this pressure decreases by 8 mbars per altitude reading until at its maximum altitude the pressure is 772 mbar. Assignment: 1. Write and execute Matlab code which create a table with one column containing pressure measurements in mbar and the other containing corresponding altitudes. The program must be well commented. 2. Plot changes in elevation with pressure. Make certain your figure has all appropriate elements and attributes.

Answer 1

P=1020:-8:772;
rho=1.15;
g=9.81;
Z=-P./(rho*g);
fprintf('%10s\t%10s\n','Pressure','Altitude')
fprintf('%10.4f\t%10.4f\n',[P;Z])
plot(P,Z)
xlabel('Pressure')
ylabel('Elevation')
grid on

HOME PLOTS APPS EDITOR PUBLISH FILE VERSIONS VIEW 5 6 Search Documentation a Vaibhav > I a I MATLAB Drive > Figure 1 x + COMMAND WINDOW CURRENT FOLDER 1 1 1 1 1 HNMOOSE 1 1 1 1 1 Elevation Pressure.mx + P=1020:-8:772; rho=1.15; g=9.81; Z=-P./(rho*g); fprintf('%10s\t%10s\n', 'Pressure', 'Altitude') fprintf("%10.4f\t%10.4f\n',[P;Z]) plot(P,Z) xlabel('Pressure') ylabel('Elevation') grid on WORKSPACE Elevation >> ElevationPressure Pressure Altitude 1020.0000 -90.4135 1012.0000 -89.7044 1004.0000 -88.9953 996.0000 -88.2861 988.0000 -87.5770 980.0000 -86.8679 972.0000 -86.1588 964.0000 -85.4496 956.0000 -84.7405 948.0000 -84.0314 940.0000 -83.3223 932.000e -82.6131 924.0000 -81.9840 916.0000 -81.1949 908.0000 -80.4858 900.0000 - 79.7766 892.0000 - 79.0675 884.0000 -78.3584 876.0000 -77.6492 868.0000 - 76.9401 860.0000 - 76.2310 852.0000 -75.5219 844.0000 - 74.8127 836.0000 - 74.1036 828.0000 -73.3945 820.0000 -72.6854 812.0000 -71.9762 804.0000 - 71.2671 796.0000 -70.5580 700 anos 60 0100 750 800 850 900 Pressure 950 1000 1050