Parameter Type | Turbojet | References | |
Parameter | Values |
| |
Ambient Parameters | Altitude | 10,000 m | Klein, [16] |
Ambient Temperature | 223.3 K | ||
Ambient Pressure | 0.2650 bar | ||
Parameters of the Gas Turbine | Mach number | 0.8 | Assumed for Design Point calculation |
Compressor Pressure Ratio | 9 | ||
Turbine Inlet Temperature | 1200 | ||
Intake Efficiency | 0.9 | ||
Compressor Efficiency | 0.9 | ||
Combustion Efficiency | 0.9 | ||
Propelling Nozzle Efficiency | 0.9 | ||
Mechanical Efficiency | 0.9 | ||
Combustion Pressure loss | 6% | ||
Nozzle inlet Temperature (Afterburner exit) | 2000 K | ||
Other parameters | Specific Heat at constant Pressure (Air) | 1.4 | Mattingly [17] |
Specific Heat at constant Pressure (Combustion Gas) | 1.157 | ||
Specific Heat Ratio of Combustion Gases | 1.333 | ||
Gas constant | 287 J/(KgK) | ||
Fuel Calorific value | 42,100 KJ/Kg | Klein [16] |