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Standard Atmosphere (ISA) Calculator

Look up ISA standard atmosphere values at any altitude: temperature, pressure, density, density ratio, and speed of sound.

About this calculator

The International Standard Atmosphere (ISA) is a reference model — not a forecast — that defines a single idealized profile of temperature, pressure, and density against altitude, used as the baseline every altimeter, performance chart, and airspeed indicator is calibrated against. This calculator reproduces the sea-level reference values and troposphere lapse-rate equation exactly as published in ICAO Doc 7488, Manual of the ICAO Standard Atmosphere — the same international standard also issued as ISO 2533:1975 — rather than an approximation: T₀ = 288.15 K, P₀ = 101,325 Pa, and a lapse rate of 0.0065 K/m (6.5°C per km) up to the 11,000 m (36,089 ft) tropopause. Below 36,089 ft (the tropopause), ISA temperature falls at a constant lapse rate of about 1.98°C per 1,000 ft as altitude increases, approximating the radiative-convective equilibrium of rising air expanding and cooling adiabatically as atmospheric pressure drops — not a change in the air's own density or in greenhouse trapping. Pressure falls with altitude too, following the barometric formula built from that same temperature profile, and pressure actually falls the fastest of the three ISA quantities: air density falls more slowly than pressure because the accompanying temperature drop partly offsets it (colder air packs more molecules into the same volume at a given pressure), while temperature itself falls the least steeply of the three, in percentage terms, through the troposphere.

Above the tropopause, ISA temperature holds constant at -56.5°C through the lower stratosphere, and pressure and density continue falling on a pure exponential decay rather than the lapse-rate-driven curve used below it. Density ratio (σ) and pressure ratio (δ) — both expressed relative to sea-level standard values — are the terms pilots actually use in performance calculations like true airspeed and engine power correction. What this tool does not account for: real-world weather, which routinely differs from ISA by 10-20°C or more; this is a reference model for comparison and calibration, not today's actual atmosphere at your location.

Inputs

ft

Troposphere: 0–36,089 ft, Stratosphere: 36,089–65,617 ft

Results

ISA Temperature

74.05°F

Pressure

696.8 hPa

Pressure20.58 inHg
Density Ratio (σ)0.7385
Air Density0.9046 kg/m³
Speed of Sound638 kt
Pressure Ratio (δ)0.6877
Temperature Ratio (θ)0.9312

Figures current as of 1993. Source: ICAO Doc 7488, Manual of the ICAO Standard Atmosphere (3rd ed.), the international standard also published as ISO 2533:1975

How to Use This Calculator
  1. Enter any altitude to see ISA standard atmosphere properties.
  2. Use ISA temperature to calculate ISA deviation (OAT − ISA temp).
  3. Density ratio is used in airspeed conversions (TAS = CAS ÷ √σ).

How the result changes with Altitude

AltitudeISA TemperaturePressure
015°C1,013.3 hPa
18,000-20.7°C506 hPa
35,000-54.3°C238.4 hPa
36,089-56.5°C226.3 hPa

What each input means

Altitude
Altitude above mean sea level in feet.

What each result means

Density Ratio (σ)
Ratio of density to sea-level standard.

How this is calculated

Worked example, using the default values

  1. ISA Temperature
    T = 15°C − 1.98°C × (Alt ÷ 1000 ft)
    15 − 1.98 × (10,000 ÷ 1000) = -4.8°C (23.3°F)
  2. Atmospheric Pressure
    P = P₀ × (T/T₀)^(g/LR)
    101325 × (268.3 / 288.15)^5.256 = 696.8 hPa (20.58 inHg)
  3. Air Density
    ρ = P / (R × T)
    69682 / (287.05 × 268.3) = 0.9046 kg/m³ (σ = 0.7385)
  4. Speed of Sound
    a = 38.967 × √(T in Kelvin)
    38.967 × √268.3 = 638 kt

Figures and sources

Engine last updated . Checked against 2 independently-derived tests — how we verify calculators. Built by Paul Gunder, a software engineer, not a licensed financial, medical, or legal professional.

Frequently Asked Questions

Why does temperature stop falling above 36,089 feet?

36,089 ft marks the tropopause, the boundary between the troposphere (where temperature falls steadily with altitude) and the stratosphere (where, in the ISA model, temperature holds constant at -56.5°C through the lower layers). Physically this reflects a real shift in atmospheric structure — the troposphere's cooling comes from rising air expanding and cooling as it climbs, a process that largely stops at the tropopause, where the temperature profile flattens out (and pressure and density, unlike temperature, keep falling continuously through both layers).

What's the practical difference between density ratio and pressure ratio?

Pressure ratio (δ) compares actual pressure to sea-level standard pressure and drives instrument calibration for altimeters. Density ratio (σ) compares actual air density to sea-level density and is what actually determines aerodynamic lift, engine power, and propeller thrust at altitude — it's why aircraft performance charts key off density altitude rather than pressure altitude, even though the two track closely in the ISA model.

Does ISA temperature ever match the real outside air temperature?

Only by coincidence on any given day — ISA is a fixed reference profile, while real atmospheric temperature varies with weather, season, latitude, and time of day, often departing from ISA by 10-20°C or more. Pilots use the difference between observed and ISA temperature (called ISA deviation) as a standardized way to describe how much warmer or colder the actual air is than the reference model, which then adjusts predicted aircraft performance.

Why does speed of sound change with altitude if the air is just thinner?

Speed of sound in air depends on temperature alone, not on pressure or density directly — it's proportional to the square root of absolute temperature. Since ISA temperature falls with altitude through the troposphere, the speed of sound falls right along with it, which is why Mach number (true airspeed divided by local speed of sound) changes with altitude even at a constant true airspeed.

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