Open main menu

Wikipedia β

Density Altitude Computation Chart[1]

Density altitude is the altitude relative to the standard atmosphere conditions (ISA) at which the air density would be equal to the indicated air density at the place of observation. In other words, density altitude is air density given as a height above mean sea level. "Density altitude" can also be considered to be the pressure altitude adjusted for non-standard temperature.

Both an increase in temperature, decrease in atmospheric pressure, and, to a much lesser degree, increase in humidity will cause an increase in density altitude. In hot and humid conditions, the density altitude at a particular location may be significantly higher than the true altitude.

In aviation, the density altitude is used to assess the aircraft's aerodynamic performance under certain weather conditions. The lift generated by the aircraft's airfoils and the relation between indicated and true airspeed are also subject to air density changes. Furthermore, the power delivered by the aircraft's engine is affected by the air density and air composition.


Aircraft safetyEdit

Air density is perhaps the single most important factor affecting aircraft performance. It has a direct bearing on:[2]

  • The lift generated by the wings — reduction in air density reduces the wing's lift.
  • The efficiency of the propeller or rotor — which for a propeller (effectively an airfoil) behaves similarly to lift on wings.
  • The power output of the engine — power output depends on oxygen intake, so the engine output is reduced as the equivalent "dry air" density decreases and produces even less power as moisture displaces oxygen in more humid conditions.

Aircraft taking off from a "hot and high" airport such as the Quito Airport or Mexico City are at a significant aerodynamic disadvantage. The following effects result from a density altitude which is higher than the actual physical altitude:[2]

  • The aircraft will accelerate slower on takeoff as a result of reduced power production.
  • The aircraft will need to achieve a higher true airspeed to attain the same lift - this implies both a longer takeoff roll and a higher true airspeed which must be maintained when airborne to avoid stalling.
  • The aircraft will climb slower as the result of reduced power production and lift.

Due to these performance issues, a plane's takeoff weight may need to be lowered or takeoffs may need to be scheduled for cooler times of the day. Wind direction and runway slope may need to be taken into account.


Density altitude is an important factor in skydiving, and one that can be difficult to judge properly even for experienced skydivers.[3] In addition to the general change in wing efficiency common for all aviation, skydiving has additional considerations. There is an increased risk due to the high mobility of jumpers (who will often travel to a drop zone with a completely different density altitude than they are used to, without being made consciously aware of it by the routine of calibrating to QNH/QFE).[4] Another factor is the higher susceptibility to hypoxia at high density altitudes, which, especially combined with the unexpected higher free fall rate, can create dangerous situations and accidents.[3] Parachutes at higher altitudes fly more aggressively, making their effective area lower, which is more demanding for the pilot's skill and can be especially dangerous for high-performance landings, which require accurate estimates and have a low margin of error before they become dangerous.[4]


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



  density altitude in meters
  atmospheric (static) pressure
  standard sea level atmospheric pressure (1013.25 hPa ISA or 29.92126 inHg US))
  true (static) air temperature in kelvins (K) [add 273.15 to the Celsius (°C)] figure
  ISA standard sea level air temperature in kelvins (K) (288.15 K)
  lapse rate (0.0065 K/m)
  gas constant (8.31432 J/mol/K)
  gravity (9.80665 m/s²)
  molar mass of dry air (0.0289644 kg/mol)

National Weather Service equation

The National Weather Service uses the following dry-air approximation of the above equation in their standards.



  density altitude in feet
  Is the station pressure (atmospheric static pressure) in inches of mercury (inHg)
  T is the station temperature (atmospheric temperature) in Fahrenheit (F)

Note that the NWS standard specifies that the density altitude should be rounded to the nearest 100 feet.

Easy formula to calculate density altitude from pressure altitude

This is an easier formula to calculate (with great approximation) density altitude from pressure altitude ..and International Standard Atmosphere temperature deviation

Density altitude in feet = pressure altitude in feet + 118.8 × (OAT − ISA_temperature)


OAT = Outside air temperature in °C
ISA_temperature = 15 °C − 1.98 °C × PA / 1000ft

considering that temperature drops at the rate of 1.98 °C each 1000 ft of altitude until the Tropopause (36000 ft), usually rounded to 2 °C

Or simply:

DA = PA + 118.8([PA/500]+OAT-15)

Or even simpler

DA = 1.24 PA + 118.8 OAT − 1782

where DA = density altitude and PA = pressure altitude where PA=Hgt+30(1013-QNH) and QNH = QNauticalHeight = Height above sea level

See alsoEdit


  1. ^ page 13-1
  2. ^ a b AOPA Flight Training, Volume 19, Number 4; April 2007; Aircraft Owners and Pilots Association; ISSN 1047-6415
  3. ^ a b Farnsworth, Musika. "Tragedy in Antarctica". Parachutist Online. Retrieved 14 January 2015. 
  4. ^ a b Walker-Radtke, Megan. "High and Fast: Understanding Density Altitude". Parachutist Online. Retrieved 14 January 2015. 


External linksEdit