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According to the recent rapid progress of high performance computing and numerical algorithm, a CFD-based aerodynamic design methodology is becoming an important tool with wind tunnel testing. The 3rd Research Center, TRDI-JDA has implemented the development and performance tests a CFD-based design system CASPER (Computational Aerodynamics System for Performance Evaluation and Research), with major domestic aircraft manufactures until March 2001. In this paper, mainly shown is part of aerodynamic and aeroelastic computed results obtained in performance tests. Actually, for the code validation, various types of aircraft and airfoil configurations are computed using the CASPER and compared well to wind tunnel testing data and other computed results. In addition, as an example of CFD multidisciplinary simulation providing the CFD data obtained in its aerodynamic characteristic module, the aeroelastic simulation can be normally performed. The CASPER can be expected to be powerful tool for conceptual and basic design stage of advanced aircraft at the next generation., 資料番号: AA0045948021, レポート番号: NAL SP-57

A numerical scheme to treat the problem of fluid-structure coupling has been developed in this study. A high order scheme based on the finite volume method (FVM) is used for fluid calculation, as well as the finite element method (FEM) for structure calculation in order to make more detailed analysis of flutter phenomena. The present method has been applied to the problem of panel flutter. For the supersonic case of M = 1.2, the flutter shows a rapid increase in amplitude into a limit cycle oscillation with a first mode. From the comparison between Euler and Navier-Stokes computation, it is clear that a boundary layer delays the growth of the flutter oscillation. For the subsonic case of M = 0.95, a static, upwardly divergent solution has been obtained, where vortices are produced due to the fluid-structure interaction in the Navier-Stokes computation., 資料番号: AA0045948020, レポート番号: NAL SP-57