Computer Center, National Aerospace Laboratory(NAL)
Computer Center, National Aerospace Laboratory(NAL)
Computer Center, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
Technical Report of National Aerospace Laboratory TR-896T
A numerical procedure based on the Euler equations for analyzing the compressible inviscid transonic flow about a wing-fuselage combination is presented in this paper. In order to treat precisely boundary conditions on the combinational surface and at infinity, the exterior of the wing-fuselage combination in physical space is mapped into a rectangular parallelepiped in a computational space and then a uniform grid is generated there. The Euler equations are solved by the finite volume method using the Runge-Kutta type scheme of the second order accuracy and the local time step technique. Three examples are presented to show the utility of the numerical procedure. Numerical results obtained by the procedure are compared with experimental results and numerical results by the NAL utility code YOKUDO-P based on the full potential equation, and it is shown that the obtained results are in good agreement with the experimental data.
Numerical Analysis of Inviscid Compressible Flows about Wing-Fuselage Combinations based on the Euler Equations
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