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