A real-time algebraic performance model for thrust vectoring nozzle is established by combining B-Spline surface fitting theory with CFD calculation. In the model, the function relationship of the nozzle performance parameters such as mass flow coefficients, thrust coefficients and efficient deflected angle with the parameters like the nozzle pressure ratio and the geometric deflected angle and the area ratio is given. With the model and aero-engine model, a model for aero-engine with thrust vectoring nozzle is obtained and the effect of the vectoring nozzle on the aero-engine is discussed.
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