Aerospace Toolbox

atmoslapse - Use Lapse Rate Atmosphere model

Syntax

[T, a, P, rho] = atmoslapse(h, g, gamma, r, l, hts, htp, rho0, p0, t0)

Description

[T, a, P, rho] = atmoslapse(h, g, gamma, r, l, hts, htp, rho0, p0, t0) implements the mathematical representation of the lapse rate atmospheric equations for ambient temperature, pressure, density, and speed of sound for the input geopotential altitude. This atmospheric model is customizable by specifying the atmospheric properties in the function input.

Inputs required by atmoslapse are:

`h`	An array of `m` geopotential heights, in meters
`g`	A scalar of acceleration due to gravity, in meters per second squared
`gamma`	A scalar of specific heat ratio
`r`	A scalar of characteristic gas constant, in joule per kilogram-kelvin
`l`	A scalar of lapse rate, in kelvin per meter
`hts`	A scalar of height of troposphere, in meters
`htp`	A scalar of height of tropopause, in meters
`rho0`	A scalar of air density at mean sea level, in kilograms per meter cubed
`p0`	A scalar of static pressure at mean sea level, in pascal
`t0`	A scalar of absolute temperature at mean sea level, in kelvin

Outputs calculated for the lapse rate atmosphere are:

`T`	An array of `m` temperatures, in kelvin
`a`	An array of `m` speeds of sound, in meters per second
`P`	An array of `m` air pressures, in pascal
`rho`	An array of `m` air densities, in kilograms per meter cubed

Examples

Calculate the atmosphere at 1000 meters with the International Standard Atmosphere input values:

[T, a, P, rho] = atmoslapse(1000, 9.80665, 1.4, 287.0531, 0.0065, ...
    11000, 20000, 1.225, 101325, 288.15 )


T =

  281.6500


a =

  336.4341


P =

  8.9875e+004


rho =

    1.1116

Assumptions and Limitations

Below the geopotential altitude of 0 km and above the geopotential altitude of the tropopause, temperature and pressure values are held. Density and speed of sound are calculated using a perfect gas relationship.

References