# Pressure altitude

Pressure altitude is the altitude in the International Standard Atmosphere (ISA) with the same atmospheric pressure as that of the part of the atmosphere in question.

The National Oceanic and Atmospheric Administration (NOAA) published the following formula for directly converting atmospheric pressure in millibars ($\mathrm {mb}$ ) to pressure altitude in feet ($\mathrm {ft}$ ):

$145366.45\left[1-\left({\frac {\text{Station pressure in millibars}}{1013.25}}\right)^{0.190284}\right].$ In aviation, pressure altitude is the height above a standard datum plane (SDP), which is a theoretical level where the weight of the atmosphere is 29.921 inches of mercury (1,013.2 mbar; 14.696 psi) as measured by a barometer. It indicates altitude obtained when an altimeter is set to an agreed baseline pressure under certain circumstances in which the aircraft’s altimeter would be unable to give a useful altitude readout. Examples would be landing at a high altitude or near sea level under conditions of exceptionally high air pressure. Old altimeters were typically limited to displaying the altitude when set between $950~\mathrm {mb}$ and $1030~\mathrm {mb}$ . Standard pressure, the baseline used universally, is $1013.25$ hectopascals ($\mathrm {hPa}$ ), which is equivalent to $1013.25~\mathrm {mb}$ or $29.92$ inches of mercury ($\mathrm {inHg}$ ). This setting is equivalent to the atmospheric pressure at mean sea level (MSL) in the ISA. Pressure altitude is primarily used in aircraft-performance calculations and in high-altitude flight (i.e., above the transition altitude).

## QNE

QNE is an aeronautical code Q code. The term refers to the indicated altitude at the landing runway threshold when $1013.25~\mathrm {mb}$ or $29.92~\mathrm {inHg}$ is set in the altimeter’s Kollsman window. In other words, it is the pressure altitude at the landing runway threshold.

Most aviation texts for PPL and CPL exams describe a process for finding the pressure altitude (in feet) using the following rule of thumb formula:

${\text{Pressure altitude (PA)}}={\text{Elevation}}+1000\times (29.92-{\text{Altimeter setting}}).$ For example, if the airfield elevation is $500~\mathrm {ft}$ and the altimeter setting is $29.32~\mathrm {inHg}$ , then

{\begin{aligned}{\text{PA}}&=500+1000\times (29.92-29.32)\\&=500+1000\times 0.6\\&=500+600\\&=1100.\end{aligned}} Alternatively,

${\text{Pressure altitude (PA)}}={\text{Elevation}}+30\times (1013-{\text{QNH}}).$ For example, if the airfield elevation is $500~\mathrm {ft}$ and the QNH is $993~\mathrm {mb}$ , then

{\begin{aligned}{\text{PA}}&=500+30\times (1013-993)\\&=500+30\times 20\\&=500+600\\&=1100.\end{aligned}} Aircraft Mode “C” transponders report the pressure altitude to air traffic control; corrections for atmospheric pressure variations are applied by the recipient of the data.

The relationship between static pressure and pressure altitude is defined in terms of properties of the ISA.