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Both increase in Temperature and increase in Humidity cause a reduction in air density. Thus in hot and humid conditions the density altitude at a particular location may be significantly higher than the geometric altitude.

Density altitude can be calculated from atmospheric pressure and temperature (assuming dry air).


\mathrm{DA} = 145426 \left[1-\left( rac{P_0/P_{SL}}{\mathrm{T}/T_{SL}} ight)^b ight]


where

\mathrm{DA}= density altitude

P_0= atmospheric (static) pressure

P_{SL}= standard sea level atmospheric pressure (1013.25 hpa)

\mathrm{T}= true (static) air temperature

T_{SL}= standard sea level air temperature(288.15 K)

b= 0.235



SIMPLER LESS ACURATE METHOD

Another simpler less acurate method to calculate density altitude is:

DA = ( 29.92 - A) x 100 + 100 ( T - ( 15 - ( 2 x H ) / 1000 ) )

A is the Altimeter setting in inches of Mercury
T is the temperature in degrees Celsius
H is the height of the airfield, or aircraft


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