Parameterized Model Design And Numerical Simulation Of Under-the-wing Nacelle For Civil Aircraft

In this paper, the monomer parametric modeling, amalgamation means of integrated modeling and the file format of Gambit read were studied proceeding from the wing nacelle monomer research, and solve issues such as the parametric curve generating discrete, discrete surfaces, surface and surface intersection integration based on the C++,Gambit. Upon the completion of complex surface modeling, gambit post-processing efficiency was improved based on the generation of body surface through the viscous grid generation.Through the above method, and reference to Langley wind tunnel test model, by adjusting the parameters, generate numerical model, and analyze the cause of the error introduced in the modeling process, the pressure coefficient distribution maps obtained through models of calculation were good agreement with experimental values by Langley models, which also further validate the feasibility to achieve methods and procedures.The above work process as follows: single parametric modeling - integration of body build, with a viscous grid generation - Gambit after-treatment-fluent calculation-parameters of contrast and performance analysis. Through the differences of the monomer shape parameter, we have chosen a more suitable monomer form according to the number M and aerodynamic parameters. After the last flow calculation, we have obtained the distribution of target parameter such as the pressure distribution and the distribution of resistance. Through the comparison of numerical simulation and test parameters we found that when the number M is low, the numerical simulations consistent with the experimental data. In the transonic, through the calculations by different SA model and the SST model we found that the numerical simulation results were better than the SA model results.Clear from the foregoing ,design parameters of under-the-wing nacelle has features of a highly efficient, methods and processes have some generality which has some reference value to under-the-wing nacelle design for civil aircraft.Numerical simulation can shorten the research cycle and save cost simultaneity. Contrast Langley test model results of numerical simulation resistance, which has some reference value to under-the-wing nacelle for civil aircraft.