| Citation: | SUN Y K，WANG L，WANG T G，et al. Optimization method for tail rotor airfoil based on SST adjoint turbulence model[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（12）：3355-3364 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0086
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A new airfoil optimization method is proposed to address the inherent defects of the frozen eddy viscosity assumption widely used in airfoil optimization and the poor accuracy of aerodynamic calculation based on Spalart-Allmaras (S-A) adjoint turbulence model. This method couples the continuous adjoint turbulence solution, Reynolds-averaged Navier-Stokes（RANS） equations closed by shear stress transfer (SST) turbulence model, and free form deformation method with dynamic grid deformation technology. Based on the proposed method, the maximum lift to drag ratio is taken as the optimization objective for the NPL9615 airfoil, and compared with that of the method of the frozen eddy viscosity assumption. The results show that the optimized airfoil based on continuous SST adjoint turbulence method increases the lift to drag ratio of the original airfoil by 16.39%, while the frozen eddy viscosity assumption method increases the lift to drag ratio of the final airfoil only by 9.84%. This indicates that the proposed method is superior to the frozen eddy viscosity assumption in terms of optimization convergence. When the turbulent kinetic energy increases significantly, the advantage of the proposed model becomes more prominent.
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