Density Altitude Calculator
Density altitude from pressure altitude and temperature — affects engine/prop performance.
How to Use
- Enter field pressure alt and OAT.
- DA is computed vs ISA.
Inputs
Result
Formulas
ISA temp
15 °C − 2 × (alt / 1000 ft)
DA (rule of thumb)
PA + 120 × (OAT − ISA)
Pressure altitude
Field elev + (29.92 − altimeter) × 1000
Impact
Higher DA = less dense air = less lift, thrust, prop efficiency
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