パネル法を用いた軸流動翼内の三次元圧縮性亜音速流れ解析

概要

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A panel method for solving three-dimensional, inviscid, compressible, subsonic flow in a axial-flow rotor is presented. The surface integral equations are often used to solve the Laplace equation with panel methods. The extension to compressible flow is to introduce the volume integral term of Green's third identity. The present method does not require the surface fitted grid. Instead it uses a rectangular grid with embedded surface panels on which boundary conditions are imposed. The Poisson problem is solved using the fast Fourier transform and the panel influence coefficient technique. The volume integral calculation is performed efficiently by using the FFT. The first numerical example is a flow about the NACA 0012 aerofoil. The results show the accuracy of the present method with a somewhat coarse grid. The second numerical example is a flow through an axial-flow rotor. The results show three-dimensional characteristics and compressible effects.
1989-01-25