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Aerodynamic shape optimization of natural-laminar-flow (NLF) nacelle for lange-range wide-body transport aircraft was investigated. Perturbed class function/shape function transformation (CST) method was used to parameter the three typical generatrix of the nacelle combined with the perturbation based transfinite interpolation method to achieve surface and space grid update. The k-ω SST (shear stress transport) turbulence model and ϒ –  Re θ  transition models was use to predict the transition location.The gradient based optimization method called Sequential Quadratic Programming was selected for the high efficiency. Natural laminar flow design was performed on three dimensional nacelles and about 45%∼55% laminar flow region was achieved by the optimization design.

Transition model based design method investigation on laminar flow nacelle