The Static Pressure at the Compressor Exit in aircraft design refers to the pressure of the air leaving the compressor section of a gas turbine engine when its velocity has been reduced to nearly zero. It is an essential parameter for understanding the thermodynamic conditions within the engine.
The formula for calculating Static Pressure (P) at the Compressor Exit is as follows:
- The Total Pressure at Compressor Exit is the combined static pressure and dynamic pressure of the air at the exit of the compressor, typically measured in Pascals (Pa) or pounds per square inch (psi).
- The Dynamic Pressure at Compressor Exit is the pressure caused by the motion of the air at the exit of the compressor, typically measured in Pascals (Pa) or psi.