The studied propeller components characteristic was obtained by use of the general components characteristic of the propeller by scaling method. Under the condition of the nonezone flight speed

the algorithm on the propeller mathematical model was presented. At the same time

by use of the scaled characteristics of propeller

the working performance curve of the fixed blade angle and the aerodynamic principle of propeller

the interaction relationships of propeller power coefficient

force coefficient

blade angle

static thrust advance ratio threshold and the designed geometric parameters of propeller were analyzed

and the algorithm on the propeller mathematical model under the state of the static force was proposed. The simulation data of the above algorithms by digital simulation was verified with the comparison of the simulation data of Gas Turbine Simulation Program (GSP) software. The results show that the proposed algorithm on the propeller model was valid. When the propeller was in the advanced state

the maximum relative error of propeller force was no more than 66059×10-6

the maximum relative error of propeller power demanded did not exceed 55098×10-6

the maximum relative error of propeller efficiency was not more than 66955×10-6.