Aerodynamic parameters | Case 3 | Case 4 | Case 5 |
Theoretical reaction heat of propellant | 28.84 | 86.52 | 114.27 |
Compressed air inlet mass flow rate (kg/s) | 0.244 | 0.174 | 0.159 |
Rotor nozzle total pressure (MPa) | 0.121 | 0.122 | 0.124 |
Rotor nozzle total temperature (K) | 437.33 | 605.03 | 855.68 |
Rotor nozzle absolute velocity/(m/s) | 203.01 | 249.39 | 304.68 |
Rotor nozzle mass flow rate (kg/s) | 0.284 | 0.234 | 0.199 |
Available moment (N∙m) | 88.27 | 89.58 | 93.03 |