Density Altitude Calculator
Calculate density altitude for aviation performance using temperature, pressure, and humidity
Calculate Density Altitude
Outside air temperature at your location
Barometric pressure from weather report
Elevation of the weather reporting station
Relative humidity percentage
Density Altitude Results
Calculation method: ICAO International Standard Atmosphere (ISA) model
Input conditions: 0.0°C, 0.0% RH, 0.0 mbar
Performance impact: Higher density altitude = reduced aircraft performance
Aviation Performance Impact
Example Calculation
Hot Summer Day at Airport
Temperature: 33°C (91°F)
Altimeter Setting: 990 mbar (29.24 inHg)
Station Elevation: 1,500 m (4,921 ft)
Relative Humidity: 41%
Calculated Results
Air Density: 0.9304 kg/m³
Density Altitude: 2,774 m (9,102 ft)
Performance Impact: Aircraft performs as if at 9,102 ft altitude
Factors Affecting Performance
Temperature
Higher temperature = lower air density
Hot air is less dense than cold air
Pressure
Lower pressure = lower air density
High altitude or low pressure systems
Humidity
Higher humidity = lower air density
Water vapor is lighter than dry air
Aviation Tips
High density altitude reduces takeoff performance
Engine produces less power at high density altitude
Propeller efficiency decreases with thin air
Wings generate less lift in low-density air
Always check density altitude before flight
Understanding Density Altitude
What is Density Altitude?
Density altitude is the altitude in the ICAO International Standard Atmosphere (ISA) that has the same air density as the actual conditions at your location. It's a critical concept in aviation because aircraft performance depends heavily on air density.
Why is it Important?
- •Determines engine power output and propeller efficiency
- •Affects wing lift generation and aircraft performance
- •Critical for takeoff and landing distance calculations
- •Essential for flight planning and safety
Calculation Method
H = 44.3308 - 42.2665 × ρ^0.234969
where H is density altitude (km) and ρ is air density (kg/m³)
Air Density Formula:
ρ = (P_d)/(R_d × T) + (P_v)/(R_v × T)
- P_d: Dry air pressure (Pa)
- P_v: Water vapor pressure (Pa)
- T: Temperature (K)
- R_d: 287.058 J/(kg·K) - dry air constant
- R_v: 461.495 J/(kg·K) - water vapor constant
Note: Based on ICAO Standard Atmosphere with sea level conditions: 15°C, 1013.25 mbar, 1.225 kg/m³