ICAO Standard Atmosphere Altitude and Pressure Calculator

Calculate Altitude & Pressure Parameters
Select Answer Mode
Altitude (H) [?]

Pressure (P) [?]

Altitude 1 (H₁) [?]

Altitude 2 (H₂) [?]

Pressure Difference (ΔP = P₂ - P₁) [?]

Pressure 1 (P₁) [?]

Pressure 2 (P₂) [?]

Altitude Difference (ΔH = H₂ - H₁) [?]

Click save settings to reload page with unique web page address for bookmarking and sharing the current tool settings

✕ clear settings

Change the answer mode for this tool by selecting altitude (H), altitiude difference (ΔH), pressure (P), or pressure difference (ΔP) as the parameter to calculate instead

Atmospheric pressure measurement products

Contents

Related Tools

User Guide

This tool which is based on the icao standard atmosphere model will calculate the air pressure at a height above or below sea level, the altitude from the atmospheric air pressure at the same level, the pressure difference between two altitudes, and the altitude difference between two atmospheric pressures.

The method and formulas used are based on the ICAO Standard Atmosphere 1993 model for use from a height of 5000 metres below mean sea level up to a height of 80,000 metres above mean sea level. The atmospheric model assumes the air is a dry ideal gas, with an atmospheric pressure of 101325 Pa and a temperature of 288.15 K at mean sea level.

In reality the atmospheric pressure, temperature & humidity level in the air are constantly changing, therefore the accuracy in determining the true altitude is limited by this. However despite the dynamic nature of the atmosphere, standard atmosphere models serve as a way of standardising measuring instruments. If every measurement instrument is calibrated with the same atmospheric model the readings can be directly compared.

Vacuum range absolute pressure measurement products

Formulas

The formulas used by this icao standard atmosphere altitude and air pressure calculator to determine each individual parameter are:

For β_b ≠ 0:

P = P_b · (1 + (β_b · (H – H_b) / T_b))^{-g / (β_b · R)}

H = ((((P / P_b) ^–^β_b ^·^{R / g} – 1) / β_b) * T_b) + H_b

For β_b = 0

P = P_b · e^{-g · (H – H_b) / (R · T_b)}

H = (ln(P / P_b) · R · T_b / -g) + H_b

ΔP = P₂ – P₁

ΔH = H₂ – H₁

Symbols

P = Atmospheric pressure at altitude H
ΔP = Atmospheric pressure difference from H₁ to H₂ altitude
P_b = Atmospheric pressure at interfaces between atmosphere transitional layers from b = 0 to 6
H = Geopotential altitude relative to mean sea level
ΔH = Geopotential altitude difference from P₁ to P₂ atmospheric pressure
H_b = Geopotential altitude from mean sea level of interfaces between atmosphere transitional layers from b = 0 to 6
T_b = Reference temperature at interface between atmosphere transitional layers from b = 0 to 6
β_b = Standard temperature lapse rate to change reference temperature (T_b) between atmosphere transitional layers from b = 0 to 6
g = Standard acceleration due to gravity = 9.90665 m/s²
R = Specific gas constant = 287.05287 J/K·kg, constant value defined by ICAO Standard Atmosphere 1993, and derived from ideal gas law equation; P = ρ·R*·T/M₀, where P = 101,325 Pa, ρ = 1.225 kg/m³, R* = 8,314.32 J/K·kmol, T = 288.15 K, M₀ = 28.964420 kg/kmol), P/(ρ·T) = R* / M₀ = R

Atmospheric Layer Constants

b	Height (m)	Pressure (Pa)	Reference Temperature (K)	Lapse Rate (K/m)
0	0	101,325	288.15	-0.0065
1	11,000	22632.0401	216.65	0
2	20,000	5474.87742	216.65	0.001
3	32,000	868.015777	228.65	0.0028
4	47,000	110.905773	270.65	0
5	51,000	66.9385281	270.65	-0.0028
6	71,000	3.95639216	214.65	-0.002

Altitude (H)

This is the geopotential height above or below mean sea level.

Pressure (P)

This is the absolute pressure of air at a particular level in the atmosphere.

Altitude 1 (H₁)

This is the initial altitude used in calculating the atmospheric pressure difference between two altitudes.

Altitude 2 (H₂)

This is the final altitude used in calculating the atmospheric pressure difference between two altitudes.

Pressure Difference (ΔP = P₂ – P₁)

This is the atmospheric pressure difference when changing altitude from H₁ to H₂.

Pressure 1 (P₁)

This is the initial atmospheric used in calculating the altitude difference between two atmospheric pressures.

Pressure 2 (P₂)

This is the final atmospheric used in calculating the altitude difference between two atmospheric pressures.

Altitude Difference (ΔH = H₂ – H₁)

This is the altitude difference when changing atmospheric pressure from P₁ to P₂.