| 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] | |