Pressure Altitude Calculator

Standard is 29.92 inHg / 1013.25 hPa.
Leave blank and the standard-day temperature for the altitude is used. Supplying a real OAT is what turns pressure altitude into density altitude.
Pressure altitude
1.2 ft
Standard Atmosphere & Aerodynamics Calculator
Pressure altitude
0.35 m
Density altitude
1.2 ft
Static pressure
101,320.76 Pa
Static pressure
1,013.208 hPa
Static pressure
29.9200 inHg
Temperature used
14.998 degC
Air density
1.224937 kg/m3
Density ratio to sea level
0.999966
Speed of sound
340.296 m/s
True airspeed
250.00 kn
Mach number
0.3779
Dynamic pressure (q)
10,130.727 Pa
Pressure altitude by the 1000 ft/inHg rule
0 ft
Worked out from ICAO Doc 7488, Manual of the ICAO Standard Atmosphere (extended to 80 km) and 3 other sources.
For planning and study. Aircraft performance must be taken from the approved flight manual for the specific aircraft; the standard atmosphere describes a reference day, not the one you are flying in.

How this is worked out

3 steps
  1. An altimeter setting of 29.92 inHg corresponds to an ISA offset of 1.2 ft.
  2. Pressure altitude = 0 ft field elevation + 1.2 ft = 1.2 ft (the 1000 ft per inHg rule of thumb gives 0 ft).
  3. At that pressure altitude p = 101320.76 Pa; with the temperature taken as standard (15 C) the density is 1.224937 kg/m3, i.e. a density altitude of 1.2 ft.

Results are general information, not financial, tax, legal, medical or engineering advice.