Online Pressure Altitude Calculator
Calculate pressure altitude in real-time for aviation purposes
Pressure Altitude Calculator
Enter the required values below to calculate pressure altitude
Pressure Altitude
This is the theoretical altitude where the atmospheric pressure matches the standard atmosphere
Pressure Altitude Formula
Pressure Altitude = (Standard Pressure - Altimeter Setting) × 1000 + Field Elevation
Standard Pressure: 29.92 inHg or 1013.25 hPa
What is Pressure Altitude
Pressure altitude is the altitude in the standard atmosphere where the pressure is the same as what you're currently experiencing. It's a critical concept in aviation for aircraft performance calculations, density altitude determination, and flight planning.
This pressure altitude calculator uses the standard aviation formula to provide accurate results in real-time. Whether you're a student pilot learning the basics or an experienced aviator doing quick calculations, this tool simplifies the process.
How It Works
Our pressure altitude calculator uses the standard formula:
Pressure Altitude = (29.92 - Altimeter Setting) × 1000 + Field Elevation
To use the calculator:
- Enter the current altimeter setting (either in inches of mercury or hectopascals)
- Input the field elevation in feet
- Click "Calculate Pressure Altitude"
- The result will display immediately in feet
This calculation is essential for determining aircraft performance characteristics and is a fundamental component of flight planning.
Frequently Asked Questions
Pressure altitude is the altitude in the standard atmosphere where the atmospheric pressure equals the current measured pressure. It's a theoretical value used in aviation for performance calculations.
Pressure altitude is critical for aircraft performance calculations. It affects true airspeed, engine performance, lift capability, and is used to calculate density altitude, which directly impacts aircraft performance.
Pressure altitude is the altitude relative to the standard pressure setting, while density altitude is pressure altitude corrected for non-standard temperature. Density altitude directly affects aircraft performance.
The standard pressure used in aviation is 29.92 inches of mercury (inHg) or 1013.25 hectopascals (hPa). This represents the average atmospheric pressure at sea level in the standard atmosphere.
You can calculate pressure altitude manually using the formula: (29.92 - Altimeter Setting) × 1000 + Field Elevation. For example, with an altimeter setting of 30.12 and field elevation of 500ft: (29.92 - 30.12) × 1000 + 500 = (-0.2 × 1000) + 500 = -200 + 500 = 300 feet.
Pilots should calculate pressure altitude during pre-flight planning to determine aircraft performance characteristics, when calculating density altitude, and when flying at altitudes where the altimeter setting is 29.92 inHg (above 18,000 feet in the US).
Higher pressure altitudes result in reduced aircraft performance. Engines produce less power, propellers are less efficient, wings generate less lift, and true airspeed is higher than indicated airspeed at higher pressure altitudes.
Yes, pressure altitude can be negative when the current atmospheric pressure is higher than standard pressure. This typically occurs when weather conditions include high pressure systems.
Pressure altitude is the baseline for calculating density altitude. Density altitude equals pressure altitude corrected for non-standard temperature. High temperatures cause density altitude to be higher than pressure altitude.
This calculator uses the standard aviation formula for pressure altitude calculation, providing results accurate enough for flight planning purposes. For official flight operations, always cross-reference with approved aircraft documentation.
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Created by the Team TheEducationistHub | Reviewed by Sadiq Saleem