Evaluation of Parallelized Unstructured-Grid CFD for Aircraft Applications

Fujita, Takeshi; Koizumi, Tepp ei; Kodera, Masatoshi; Nakahashi, K.; Iwamiya, Toshiyuki; Nakamura, Takashi

doi:10.1016/b978-044450680-1/50049-8

Cited by 4 publications

(1 citation statement)

References 7 publications

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“…The TAS code is fully vectorized with an edge-coloring technique [20] and parallelized with a message passing interface (MPI) and domain partitioning technique [21].…”

Section: Cfd Solver and Meshmentioning

confidence: 99%

Multidisciplinary Design Exploration for a Winglet

Takenaka¹,

Hatanaka²,

Yamazaki³

et al. 2008

Journal of Aircraft

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In this paper, we describe a multidisciplinary design exploration technique with a high-fidelity analysis applied to the winglet design for a commercial jet aircraft. The minimization of the block fuel at a fixed aircraft operating range and a maximum takeoff weight were selected as design objectives. Both objective functions were estimated from a computational fluid dynamics based aerodynamic drag and a finite element method based structural weight. Various computational fluid dynamics and optimization techniques, such as the midfield drag decomposition method, the automatic computational fluid dynamics mesh generation, the kriging surrogate model, and multi-objective genetic algorithms, were integrated and applied to the detail design exploration. Computational fluid dynamics with the midfield drag decomposition method showed the effect on wave, induced, and profile drag components due to different winglet defining parameters. Practical design decision was explored based on the Pareto front and some design criteria that were uncovered within the numerical optimization. Finally, the design process was validated through the validation of the kriging approximation and aerodynamic characteristics based on the wind-tunnel test. Nomenclaturechord length of wing C wr = root chord length of winglet C wt = tip chord length of winglet F ind = induced drag seed vector F s;H = entropy & enthalpy drag seed vector k w = form factor of winglet l w = span length of winglet M = Mach number n = unit normal vector to a surface P = pressure R = gas constant Re c = Reynolds number based on mean aerodynamic chord S ref = reference wing area S wet = wetted area t=c = winglet thickness divided by local chord length u = velocity vector V = control volume W = structural weight WA = Trefftz plane = specific heat ratio s = entropy variation H = enthalpy variation w25 = winglet sweep angle at 25% chord length l = laminar viscosity coefficient t = turbulent viscosity coefficient = density Subscript 1 = freestream value

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“…The TAS code is fully vectorized with an edge-coloring technique [20] and parallelized with a message passing interface (MPI) and domain partitioning technique [21].…”

Section: Cfd Solver and Meshmentioning

confidence: 99%