Numerical Simulations of Compressible Flow

航空宇宙工学の分野において、設計・開発に伴う労力を軽減する手段として数値シミュレーションは重要な位置を占めており、高精度な数値解析法の開発が必要とされている。本研究はそうした開発の一環として、二次元の数値解法を遷音速タービン翼列と超音速排気ノズルに適用し、その流れの解明を行った。さらに、三次元解析への基礎研究として、本解法の三次元への拡張も試みた。In recent years, computational fluid dynamics have become a powerful tool for the design of fluid machinery, airplane and so on. In this point of view, the development of the highly accurate numerical solver is important. In this study, the two-dimentional, conservational formed Navier-Stokes equations are solved for the flows in transonic cascades and in super-sonic exhaust nozzle. These equations are discretized by a cell-centered finite volume method. The inviscid fluxes at cell interfaces are evaluated by a highly accurate TVD scheme based on the Harten-Yee. The viscous fluxes are determined in a central differencing manner. Furthermore, this solver is applied to the three-dimensional flows