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

- 500 to 1200 millibar atmospheric pressure logger with RS232 interface
- Wide barometric range high precision pressure transmitter
- 30 psi barometric pressure transducer with 0-10Vdc out
- 500-1100 mbar absolute 0-10Vdc out air pressure sensor for meteorological use

## Related Tools

- US Standard Atmosphere Altitude and Pressure Calculator
- Pressure unit conversion
- Height unit conversion

## 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**

- 35X Flush Diaphragm Digital Output Pressure Sensor
- 25 Ed Flame Proof Flush Diaphragm Pressure Transmitter
- 50 kPa absolute vacuum air pressure gauge with 1/4 NPT male fitting
- Vacuum insulation 15 psi absolute range millivolt output pressure sensor for air extraction use

### 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 / (βb · R)}

H = ((((P / P_{b}) ^{–}^{βb} ^{ · }^{R / g} – 1) / β_{b}) * T_{b}) + H_{b}

For β_{b} = 0

P = P_{b} · e^{-g · (H – Hb) / (R · Tb)}

H = (ln(P / P_{b}) · R · T_{b} / -g) + H_{b}

ΔP = P_{2} – P_{1}

ΔH = H_{2} – H_{1}

#### Symbols

- P = Atmospheric pressure at altitude H
- ΔP = Atmospheric pressure difference from H
_{1}to H_{2}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 P
_{1}to P_{2}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/s
^{2} - 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/M
_{0}, where P = 101,325 Pa, ρ = 1.225 kg/m^{3}, R* = 8,314.32 J/K·kmol, T = 288.15 K, M_{0}= 28.964420 kg/kmol), P/(ρ·T) = R* / M_{0}= 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 (H_{1})

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

### Altitude 2 (H_{2})

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

### Pressure Difference (ΔP = P_{2} – P_{1})

This is the atmospheric pressure difference when changing altitude from H_{1} to H_{2}.

### Pressure 1 (P_{1})

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

### Pressure 2 (P_{2})

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

### Altitude Difference (ΔH = H_{2} – H_{1})

This is the altitude difference when changing atmospheric pressure from P_{1} to P_{2}.

**Atmospheric pressure measurement products**

- Air flow normalising calculation barometric pressure transmitter
- Atmospheric, Barometric Range Scaled Volts Signal Out Pressure Transducers
- Atmospheric range for 4-20mA pressure sensor
- Atmospheric Pressure Data Loggers