Aviation cockpit
Home/Calculators/Density Altitude
Aviation

Density & Pressure Altitude Calculator

Enter field elevation and QNH (1013.25 hPa ISA), or pressure altitude directly. OAT in °C or °F. ISA lapse rate: 15 °C at MSL, −2 °C per 1,000 ft.

609.6 m AMSL

Low 980ISA 1013.25High 1040

Formula: Pressure Alt = Elev + (1013.25 − QNH) × 30 ft · Density Alt = PA + 120 × (OAT − ISA temp). ISA temp = 15 − 2 × (PA / 1000) °C.

Results

Pressure Altitude
2,000 ft
From 2,000 ft elev @ 1013.25 hPa QNH
ISA Temperature @ PA
11 °C (51.8 °F)
OAT deviation: +17 °C from ISA
Density Altitude
4,040 ft
+2040 ft above pressure altitude due to temperature
High density altitude — expect noticeably reduced climb and take-off performance.
Need wind correction and fuel burn too? Open the full E6B flight computer →

How it works

Pressure altitude

When you set your altimeter to 1013.25 hPa (29.92 inHg), the reading is pressure altitude. From field elevation, we derive it as: elevation + (1013.25 − QNH) × 30 ft per hPa.

ISA standard atmosphere

At mean sea level under ISA, temperature is 15 °C at 1013.25 hPa. Temperature decreases 2 °C for every 1,000 ft of pressure altitude — not every 100 ft. At 5,000 ft PA, ISA temp is 5 °C.

Density altitude

Hot air is less dense, so aircraft perform as if they are at a higher altitude. The rule-of-thumb used by pilots and CASA training materials: add 120 ft to pressure altitude for every 1 °C that OAT exceeds ISA at that level.