陰関数定理を利用した翼形状の最適化

概要

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An airfoil shape is optimized by finding its design variables such that an objective function is minimized. The sequential quadratic programming procedure is used for the minimization. Each search of the sequential quadratic programming procedure requires calculation of the gradient of the objective function with respect to the design variables. The gradient is calculated by using the implicit function theorem. This method greatly reduces CPU time for the gradient calculation. Regardless of the design variables number, the calculation costs as much CPU time as flow simulation. An optimization example for an axial compressor cascade is presented.
日本応用数理学会の論文
2000-03-15