Temperature, Pressure, and Density Danielle Hettmann and Chris Saleh SYST460 – Fall 2011.

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Presentation transcript:

Temperature, Pressure, and Density Danielle Hettmann and Chris Saleh SYST460 – Fall 2011

Static temperature: measure of the temperature at the surface of the aircraft Ambient temperature: measure of the temperature of the air in the region surrounding the aircraft

rule of thumb: ambient temperature drops 1 ˚ C for every 1000 feet increase in altitude Ambient temperature varies with altitude: Below 36,089 feet: ambient temperature (˚R) = ˚ * (altitude/1000) Above 36,089 feet: ambient temperature (˚R) = ˚ Temperature Ratio Below 36,089 feet, Tamb/TSeaLevel = θ = 1 – ( X 10 ^-6) * pressure altitude Above 36, 089 feet, Tamb/TSeaLevel = θ = Delta ISA θ = (T amb + ∆ISA) / (T SeaLevel + ∆ISA)

Static Pressure: Measure of the pressure at the surface of the aircraft Ambient Pressure: Measure of the pressure of the air in the region surrounding the aircraft

Pressure Ratio :  =P amb / P SeaLevel Below 36,089 feet, the Ambient Pressure (lb/ft2) = (1 - ˚ * 6.88 X * Pressure Altitude) 5.26 Above 36,089 feet, the Ambient Pressure (lb/ft2) = e ( ( – Pressure Altitude)/ )

Ambient Density: Measure of the density of the air in the region surrounding the aircraft Density Ratio: =  (Slugs/ft3) =  amb /  SeaLevel Boyles Law: Density (  ), pressure (  ), temperature (θ)  =  / θ