標(biāo)題: Titlebook: EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics; Proceedings of the B Jacques Periaux,Gabriel Bugeda,Bruno Stouffl [打印本頁(yè)] 作者: 遮陽傘 時(shí)間: 2025-3-21 19:45
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics影響因子(影響力)
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics影響因子(影響力)學(xué)科排名
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics網(wǎng)絡(luò)公開度
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics網(wǎng)絡(luò)公開度學(xué)科排名
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics被引頻次
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics被引頻次學(xué)科排名
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics年度引用
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics年度引用學(xué)科排名
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics讀者反饋
書目名稱EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics讀者反饋學(xué)科排名
作者: regale 時(shí)間: 2025-3-21 20:49 作者: 臭名昭著 時(shí)間: 2025-3-22 03:41 作者: Explicate 時(shí)間: 2025-3-22 06:45 作者: 沐浴 時(shí)間: 2025-3-22 09:42
Stochastic Processes: General TheoryWe propose the use of nonlinear GMRES in order to solve the optimality conditions in unconstrained optimization problems. We show academic examples and industrial applications of shape optimization in potential flows.作者: PATHY 時(shí)間: 2025-3-22 15:37
Definition of the Problems for the AnalysisDuring the last years with a constant increasing activity, an increasing number of scientific meetings gathering expert researchers and engineers have taken place in the field of Computational Fluid Dynamics.作者: PATHY 時(shí)間: 2025-3-22 17:05
Direct Optimization of Transonic AirfoilsThe paper reports on the numerical procedure for the optimization of transonic airfoils developed in ALN D.V.D. within BRITE/EURAM AERO-0026 contract. Results for the solution of test case T6 of the workshop are presented.作者: delusion 時(shí)間: 2025-3-22 23:53
Comparison of some Optimization Methods and their Application in the Shape Optimization of Lifting AWe propose the use of nonlinear GMRES in order to solve the optimality conditions in unconstrained optimization problems. We show academic examples and industrial applications of shape optimization in potential flows.作者: Generalize 時(shí)間: 2025-3-23 05:05
EUROPT — A European Initiative on Optimum Design Methods in Aerodynamics978-3-322-86570-0Series ISSN 0179-9614 作者: 不適當(dāng) 時(shí)間: 2025-3-23 08:44
Stochastic Dominance and Risk Measures,logies have been proposed (see [1],[2],[3],[4]). These new methodologies can be used for the computation of different academic and industrial designs like nozzles, airfoils and wing-body configurations with inviscid flows modeled by the (full) potential and Euler equations.作者: 易怒 時(shí)間: 2025-3-23 10:26 作者: hangdog 時(shí)間: 2025-3-23 17:54
Introductionlogies have been proposed (see [1],[2],[3],[4]). These new methodologies can be used for the computation of different academic and industrial designs like nozzles, airfoils and wing-body configurations with inviscid flows modeled by the (full) potential and Euler equations.作者: Mystic 時(shí)間: 2025-3-23 18:28 作者: Mortar 時(shí)間: 2025-3-23 23:29
https://doi.org/10.1007/978-3-322-86570-0Numerik; Str?mung; Str?mungsmechanik; aerodynamics; computer; dynamics; optimization; fluid- and aerodynami作者: BRAND 時(shí)間: 2025-3-24 04:00 作者: CRATE 時(shí)間: 2025-3-24 10:30
Stochastic Dominance and Risk Measures,logies have been proposed (see [1],[2],[3],[4]). These new methodologies can be used for the computation of different academic and industrial designs like nozzles, airfoils and wing-body configurations with inviscid flows modeled by the (full) potential and Euler equations.作者: obsession 時(shí)間: 2025-3-24 13:29
Data-Driven Low-Order Stochastic Models,f airfoils represented by cubic splines and operating at subsonic and transonic conditions. It is shown that the number of iterations has been multiplied by three between the subsonic and the transonic case. For the optimization problem, the drag objective function is penalized to take into account 作者: MEAN 時(shí)間: 2025-3-24 16:40
https://doi.org/10.1007/978-1-4612-2528-7: ’design patches’, whose surface is derived from given pressures and ’analysis patches’, whose pressures are derived from given surface. To solve such ’mixed’ problems the panel code is embedded into an iteration loop, which minimizes the sum of squared pressure deviations. The geometry representat作者: wreathe 時(shí)間: 2025-3-24 19:40
Sampling Methods for Processes,d is based on full-potential theory and minimizes a cost function weighting the deviations from specified target pressure distributions for each design condition in a least squares sense. Deviations from specified target pressure distributions (residuals) are translated into airfoil geometry correct作者: 凈禮 時(shí)間: 2025-3-25 01:55
Realisierbarkeit von Abbildungen, an adjoint state method to an upwind discretization with differentiable flux splitting. Thus, we construct a descent method with a discrete gradient computed exactly. In order to improve the performances, a method for increasing the number of unknowns, and relying on a multilevel idea is also imple作者: callous 時(shí)間: 2025-3-25 04:36 作者: musicologist 時(shí)間: 2025-3-25 09:17 作者: 首創(chuàng)精神 時(shí)間: 2025-3-25 13:57 作者: maintenance 時(shí)間: 2025-3-25 19:44
Limit Theorems for Stopped Random Walks,or each test case, the reasons that make the test case interesting for the workshop, the special difficulties for the resolution, its possible interest for a future workshop in the context of the ECARP Brite/Euram project and a comparison of the results presented by different contributors.作者: 使困惑 時(shí)間: 2025-3-25 21:20
0179-9614 ts of the contributors during a workshop which took place in Barcelona in June 1992. This workshop was organized in the framp- work of the Brite/Euram Aeronautics project "Optimum Design in Aerodynamics" (AERO-89-0026). The project brought together nine European partners from Acade- my and Industry 作者: VEIL 時(shí)間: 2025-3-26 02:43
Realisierbarkeit von Abbildungen,computed exactly. In order to improve the performances, a method for increasing the number of unknowns, and relying on a multilevel idea is also implemented. These methods are applied to shape optimization of a 2-D nozzle in a subsonic or transonic Eulerian flow; inverse and optimization problems are successively considered.作者: 表皮 時(shí)間: 2025-3-26 05:04 作者: 灌溉 時(shí)間: 2025-3-26 09:28
Shape Optimization of an Euler Flow in a Nozzlecomputed exactly. In order to improve the performances, a method for increasing the number of unknowns, and relying on a multilevel idea is also implemented. These methods are applied to shape optimization of a 2-D nozzle in a subsonic or transonic Eulerian flow; inverse and optimization problems are successively considered.作者: diskitis 時(shí)間: 2025-3-26 16:04
Description of the Graphic Software Used for the Workshope International Center for Numerical Methods in Engineering (CIMNE). CIMNE is a research organization based in UPC and devoted to promote training and R & D activities in the field of numerical methods and their applications for solution of engineering problems.作者: 低能兒 時(shí)間: 2025-3-26 18:58
Conference proceedings 1997ch took place in Barcelona in June 1992. This workshop was organized in the framp- work of the Brite/Euram Aeronautics project "Optimum Design in Aerodynamics" (AERO-89-0026). The project brought together nine European partners from Acade- my and Industry with big experience in numerical optimizatio作者: AV-node 時(shí)間: 2025-3-26 23:28 作者: 修剪過的樹籬 時(shí)間: 2025-3-27 02:30 作者: 泥土謙卑 時(shí)間: 2025-3-27 08:33
Sampling Methods for Processes,i-point design problem is demonstrated for a two-point reconstruction test case. First results of a two-point example airfoil design case are presented. The applicability of the residual correction methodology to 3D single-point wing design is demonstrated as well.作者: expound 時(shí)間: 2025-3-27 12:16 作者: 使熄滅 時(shí)間: 2025-3-27 15:36
Wing Design with a 3D-Subsonic Inverse Panel Methodictious design section inside the body and projecting it onto the body at a specified direction. Several examples demonstrate the power of the method and the usefulness to actual aircraft design problems.作者: 敬禮 時(shí)間: 2025-3-27 18:21
A Residual Correction Method Applied to 2D Multi-Point Airfoil Design and 3D Single-Point Wing Desigi-point design problem is demonstrated for a two-point reconstruction test case. First results of a two-point example airfoil design case are presented. The applicability of the residual correction methodology to 3D single-point wing design is demonstrated as well.作者: 丑惡 時(shí)間: 2025-3-28 00:26
EUROPT — A European Initiative on Optimum Design Methods in AerodynamicsProceedings of the B作者: anagen 時(shí)間: 2025-3-28 04:34
0179-9614 ve worked in the field are to be paid to apply numerical optimization to automated design of real problems, namely aerodynamic shapes in Aerospace Engineering. For the above reasons, it was evid978-3-322-86572-4978-3-322-86570-0Series ISSN 0179-9614 作者: extemporaneous 時(shí)間: 2025-3-28 09:55 作者: guardianship 時(shí)間: 2025-3-28 14:01
d of any additional analysis. This information allows to build up a finite element mesh for the new design with an specified and controlled level of error. The robustness and reliability of the proposed methodology is checked out with some 2D application examples.作者: tolerance 時(shí)間: 2025-3-28 14:38 作者: 項(xiàng)目 時(shí)間: 2025-3-28 19:50 作者: 巨碩 時(shí)間: 2025-3-29 00:20
Single-Pass Method for the Solution of the 2-D & 3-D Inverse Potential Problemtions of the grid lines, after the flow field has been determined. The 2-D case is treated as a particular case of the general 3-D one. The method has been applied to both 2-D and 3-D reproduction cases of the present workshop with very satisfactory results.作者: bourgeois 時(shí)間: 2025-3-29 05:21 作者: 手銬 時(shí)間: 2025-3-29 07:28
Contribution to Problems T4 and T6 Finite Element GMRES and Conjugate Gradient Solversf airfoils represented by cubic splines and operating at subsonic and transonic conditions. It is shown that the number of iterations has been multiplied by three between the subsonic and the transonic case. For the optimization problem, the drag objective function is penalized to take into account 作者: 腫塊 時(shí)間: 2025-3-29 13:31
Wing Design with a 3D-Subsonic Inverse Panel Method: ’design patches’, whose surface is derived from given pressures and ’analysis patches’, whose pressures are derived from given surface. To solve such ’mixed’ problems the panel code is embedded into an iteration loop, which minimizes the sum of squared pressure deviations. The geometry representat作者: NICHE 時(shí)間: 2025-3-29 18:32
A Residual Correction Method Applied to 2D Multi-Point Airfoil Design and 3D Single-Point Wing Desigd is based on full-potential theory and minimizes a cost function weighting the deviations from specified target pressure distributions for each design condition in a least squares sense. Deviations from specified target pressure distributions (residuals) are translated into airfoil geometry correct作者: outer-ear 時(shí)間: 2025-3-29 22:59 作者: moratorium 時(shí)間: 2025-3-30 02:37
Aerodynamic Shape Optimization Using Automatic Adaptive Remeshingzed by the Finite Element Method. A suitable and very general technique for the parametrization of the optimization problem using B-splines to define the boundary is first presented. Then, mesh generation using the advancing front method, the estimation of error and the mesh refinement criterion are作者: nephritis 時(shí)間: 2025-3-30 07:52
