ThermophysicalData
Maple 2021 enhances the ThermophysicalData package with reference atmosphere models. These describe how air pressure, temperature, density, and molecular weight typically change with altitude.
restart:withThermophysicalData
Atmosphere,Chemicals,CoolProp,PHTChart,Property,PsychrometricChart,TemperatureEntropyChart
Two models are available—the 1976 US Standard Atmosphere (the default), and the International Standard Atmosphere.Both are similar but are valid between different altitude limits.
Altitude can be specified as geopotential (the default) or geometric. Geopotential altitude adjusts for the variation in gravity with altitude.
Atmosphere⁡3⁢km,all,altitudetype=geopotential
268.6500⁢K,70108.52215⁢Pa,0.9091219586⁢kgm3,328.5779005⁢ms,0.00001693718731⁢Pa⁢s
Atmosphere⁡3⁢km,all,altitudetype=geometric
268.6591984⁢K,70121.13970⁢Pa,0.9092544424⁢kgm3,328.5835256⁢ms,0.00001693764616⁢Pa⁢s
Altitude is assumed to be in meters if no units are provided.
Atmosphere⁡3000,all,altitudetype=geometric
268.6591984,70121.13970,0.9092544424,328.5835256,0.00001693764616
Here we plot air temperature, viscosity, density, pressure, and speed of sound as functions of altitude.
plotOpts≔size=400,400,background=LightGrey,axis=gridlines=10,color=white,titlefont=Arial,16,axesfont=Arial,labelfont=Arial,12,axes=boxed,labeldirections=horizontal,vertical:
plot⁡Atmosphere⁡x,temperature,x,x=0..80000,labels=Temperature (K),Altitude (m),plotOpts
plot⁡Atmosphere⁡x,viscosity,x,x=0..80000,labels=Viscosity (Pa s),Altitude (m),plotOpts
plot⁡Atmosphere⁡x,density,x,x=0..80000,labels=Density (kg/m3),Altitude (m),plotOpts
plot⁡Atmosphere⁡x,pressure,x,x=0..80000,labels=Pressure (Pa),Altitude (m),plotOpts
plot⁡Atmosphere⁡x,speedofsound,x,x=0..80000,labels=Speed of Sound (m/s),Altitude (m),plotOpts
A skydiver free-falls through the atmosphere. The descent is modeled by this differential equation.
de≔m ⅆ2ⅆt2yt=−m⋅g+12⁢A⋅Cd⋅ρt⋅velt2,velt=−ⅆⅆtyt:
where
m is mass
g is acceleration due to gravity
Cd is the drag coefficient
ρ(t) is the air density
Air density ρ varies with altitude.
ρ≔t→Atmosphere:-Propertydensity,y⁡t:
Define the other parameters:
A≔1:m≔85:Cd≔0.58:g≔9.8:
Numerically solve the differential equation.
sol≔dsolve⁡de,vel⁡0=0,y⁡0=22000,D⁡y⁡0=0,numeric,known = Atmosphere:-Property, range=0..250
sol≔procx_rkf45_dae...end proc
Plot the altitude vs. time, velocity vs. time, and velocity vs. altitude.
plots:-odeplot⁡sol,t,y⁡t,t=0..250,labels=time (s),Altitude (m),plotOpts
plots:-odeplot⁡sol,t,vel⁡t,t=0..250,plotOpts
plots:-odeplot⁡sol,vel⁡t,y⁡t,t=0..250,plotOpts
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