The Total Pressure at Compressor Exit in aircraft design refers to the combined static pressure and dynamic pressure of the air leaving the compressor section of a gas turbine engine. It is a crucial parameter for assessing the performance of the engine.
The formula for calculating the Total Pressure at Compressor Exit is as follows:
- Static Pressure at Compressor Exit: This is the static air pressure at the exit of the compressor and is typically measured in Pascals (Pa) or pounds per square inch (psi).
- Dynamic Pressure at Compressor Exit: This is the dynamic pressure of the air at the exit of the compressor, typically measured in Pascals (Pa) or psi.