A method for calculating the effective vectoring angle and flow coefficient of an axisymmetric thrust-vectoring nozzle

In order to analyze the influence of thrust vectoring on engine performance, we establish the mathematical model of effective vectoring angle and flow coefficient by analysing the geometric relative variation, and present a calculation method based on this model. We explain in detail the principle of this model and the calculation results in the full paper; in this abstract, we just add some pertinent remarks to listing the two topics of explanation; (1) the formulation of the mathematical model, (2) computation of the performance of four types of nozzles. Under topic 1, we derived the model by giving Equations (1), (3) and (4), and Equation (13). The effective vectoring angle can be obtained by Equations (1), (3) and (4), and the flow coefficient can be obtained by Equation (13). In topic 2, the effective vectoring angles and flow coefficients of four types of nozzles are computed by this model. The calculation results by our model and a CFD-based model and the experimental data are presented in Figures 2 through 9 for comparison. It can be seen that our model can be used for the nozzle without afterburner and the long nozzle with afterburner, and that the precision by our model for the long nozzle is higher than the precision for the short nozzle.