Write a MATLAB program to generate standard atmosphere values for the troposphere and stratosphere which range from sea level (h = 0 km) to 47 km in 1 km steps. Your output should be:

Standard Atmosphere Table with columns: o Geopotential altitude, h (km) o Geometric altitude, hG (km) o Temperature, T (K) o Density, (kg/m3 ) o Pressure, p (N/m2 )

Plots of geopotential altitude, h, in km vs: o Temperature, T, (K) o Density, , (kg/m3 ) o Pressure, p, (N/m2 )

The gradient layers are the troposphere (0 km to 11 km) and the stratosphere (25 km to 47 km).

Start at sea level (h = 0 km) using standard sea level values given as:

Temperature, TSL = 288.16 K

Density, SL = 1.225 kg/m3

Pressure, pSL = 1.01325x105 N/m2

Acceleration due to gravity, go = 9.80065 m/s2

Gas constant, R = 287 J/(kg*K)

Use the following equations, derived from the hydrostatic equation and the equation of state:

-9o-1 p17 where a is the lapse rate for the gradient layer given as: a =-6.5 x 10-3 K/m (troposphere) a = 3.0 x 10-3 K/m (stratosphere) Isothermal Layer The isothermal (meaning constant temperature) layer exists from h = 11 km to h = 25 km. Use the following equations, derived from the hydrostatic equation and the equation of state: -= e(#)(h-h.) P: -9o-1 p17 where a is the lapse rate for the gradient layer given as: a =-6.5 x 10-3 K/m (troposphere) a = 3.0 x 10-3 K/m (stratosphere) Isothermal Layer The isothermal (meaning constant temperature) layer exists from h = 11 km to h = 25 km. Use the following equations, derived from the hydrostatic equation and the equation of state: -= e(#)(h-h.) P