標(biāo)題: Titlebook: Boundary Element Methods in Engineering; Proceedings of the I Balkrishna S. Annigeri,Kadin Tseng Conference proceedings 1990 Springer-Verla [打印本頁] 作者: 欺侮 時(shí)間: 2025-3-21 18:58
書目名稱Boundary Element Methods in Engineering影響因子(影響力)
書目名稱Boundary Element Methods in Engineering影響因子(影響力)學(xué)科排名
書目名稱Boundary Element Methods in Engineering網(wǎng)絡(luò)公開度
書目名稱Boundary Element Methods in Engineering網(wǎng)絡(luò)公開度學(xué)科排名
書目名稱Boundary Element Methods in Engineering被引頻次
書目名稱Boundary Element Methods in Engineering被引頻次學(xué)科排名
書目名稱Boundary Element Methods in Engineering年度引用
書目名稱Boundary Element Methods in Engineering年度引用學(xué)科排名
書目名稱Boundary Element Methods in Engineering讀者反饋
書目名稱Boundary Element Methods in Engineering讀者反饋學(xué)科排名
作者: 放逐 時(shí)間: 2025-3-21 22:32
Time and Frequency Domain Aerodynamics for Flutter of Helicopter Rotors in Hovery-element formulation for unsteady potential incompressible flows is introduced. The results obtained for the aerodynamic forces, for pitch and flap, are compared with those typically used in the flutter analysis of rotors, (which are obtained using a strip-theory extension of Loewy’s formulation [3作者: Canyon 時(shí)間: 2025-3-22 04:15 作者: 凝結(jié)劑 時(shí)間: 2025-3-22 05:30
A General Purpose Fixed-Wing and Rotary-Wing Compressible Aerodynamics Analysis Method in which the wake and/or field influence is coupled into the linear Laplace solver through the boundary conditions. There are a number of advantages in using this approach. For instance, since the wake effect is “seen” as an induced velocity, any methodology that can provide this information may be作者: 揭穿真相 時(shí)間: 2025-3-22 09:49 作者: 機(jī)密 時(shí)間: 2025-3-22 14:25
Panel Methods for Multiple-Rotor Aerodynamicson. The earlier of the two is a full surface, time marching panel scheme based on Morino’s formulation. It has been implemented only for low speed (incompressible) flow. The second scheme uses an iterative coupling of the rotor velocity fields, decomposed into harmonics. Each field harmonic is compu作者: 推崇 時(shí)間: 2025-3-22 17:32 作者: Salivary-Gland 時(shí)間: 2025-3-23 00:16
A Vortex Method for Predicting Unsteady Flow and Boundary Layer Development Around an Airfoilminar and turbulent boundary layers are treated. By using even a rather small computer, reasonable prediction of starting flows around an airfoil of NACA23012 are obtained for various angles of attack either with or without boundary layer separation. The emphasis in the following article will be on 作者: ORE 時(shí)間: 2025-3-23 03:15 作者: 蝕刻術(shù) 時(shí)間: 2025-3-23 06:31
A Unified Approach for Potential and Viscous Flows in Fixed-Wing and Rotary-Wing Aerodynamicsential aerodynamics and to introduce an extension of the formulation to compressible viscous flows. For the sake of simplicity, details of the formulation are given only for incompressible flows. For compressible flows, the formulations are only outlined. Also, because of space limitations no numeri作者: 脫落 時(shí)間: 2025-3-23 11:00 作者: 詞匯表 時(shí)間: 2025-3-23 16:36 作者: Leaven 時(shí)間: 2025-3-23 20:52
Advanced Boundary Element Methods for Incompressible Thermoviscous Flowitten exclusively in terms of velocities and temperatures, thus eliminating the need for the computation of gradients. Furthermore, with the introduction of reference velocities and temperatures, volume modeling can often be confined to a small portion of the problem domain, typically near obstacles作者: 針葉樹 時(shí)間: 2025-3-23 23:05
A Boundary Element Model for the Taylor-Couette Instabilityiety of flow conditions occurs. Such phenomenon is usually referred to as the Taylor-Couette instability [1]. For low values of the relative angular speeds of the cylinders the only non zero-velocity component is the azimuthal velocity .θ and the streamlines are concentric circumferences in a plane 作者: 刺激 時(shí)間: 2025-3-24 05:07
Boundary Element Methods for the Navier Stokes Equationsrmined with finite difference algorithms. These algorithms are providing excellent data, hut at extrodinary computer costs. Boundary element methods provide an alternative to finite difference methods. In this paper, a boundary element method for the Navier-Stokes equations is described. This method作者: synovial-joint 時(shí)間: 2025-3-24 08:01 作者: 禍害隱伏 時(shí)間: 2025-3-24 14:05 作者: concubine 時(shí)間: 2025-3-24 14:59
4 Neutron sources and spectrometers,], although a boundary-element formulation has been used by Kwon [2] for a flutter analysis). The results demonstrate that Loewy’s formulation [3] yields results that are considerably different from those obtained with the more accurate model introduced here.作者: 表臉 時(shí)間: 2025-3-24 21:03 作者: 袋鼠 時(shí)間: 2025-3-25 02:11 作者: cloture 時(shí)間: 2025-3-25 05:18
11 Average neutron resonance parameters,e which is constricted in aim at the use of the simplest boundary element, i.e., the constant element. The solution method is applied to several examples on the forced horizontal oscillation of a fluid in containers and generation, propagation, run-up and reflection on a vertical wall of a solitary water wave.作者: Granular 時(shí)間: 2025-3-25 07:32 作者: 熱心 時(shí)間: 2025-3-25 13:34 作者: 蚊子 時(shí)間: 2025-3-25 16:50
4 Neutron sources and spectrometers, not require a body-fitted field grid. This is of considerable advantage for flows around complex configurations. In addition, this new formulation is essentially based on the concept of velocity decomposition. Therefore, future extension to allow for viscous effects may be accomodated in a fairly straight-forward manner.作者: 他去就結(jié)束 時(shí)間: 2025-3-25 22:19
4 Neutron sources and spectrometers,accurate and computational efficient compared to finite difference methods. In this paper, the method of frequency domain computation is discussed. Selected results from 2D and quasi 3D flow in steady, and unsteady states are presented.作者: Anonymous 時(shí)間: 2025-3-26 04:04
11 Average neutron resonance parameters,al approaches were used to study this problem [2, 3]. Because of this lack of data on the wake geometry, the approaches used in the non-axial flow analysis are typically experimental [4, 5, 6]: a free-wake analysis is included in this paper. The formulation used is closely related to that of Morino and Bharadvaj [8].作者: AGGER 時(shí)間: 2025-3-26 06:46
Boundary Integral Formulations of the Scalar and Vector Wave Equations with Arbitrary Moving Boundarnd spatial derivatives of the surface distribution, respectively. Explicit formulas for these general operators are then derived for some scalar and vector wave equations from aerodynamics, aeroacoustics and electrodynamics.作者: 流出 時(shí)間: 2025-3-26 08:40
A General Purpose Fixed-Wing and Rotary-Wing Compressible Aerodynamics Analysis Method not require a body-fitted field grid. This is of considerable advantage for flows around complex configurations. In addition, this new formulation is essentially based on the concept of velocity decomposition. Therefore, future extension to allow for viscous effects may be accomodated in a fairly straight-forward manner.作者: 無情 時(shí)間: 2025-3-26 13:30
Turbomachinery Blade Loading Prediction Using the Panel Methodaccurate and computational efficient compared to finite difference methods. In this paper, the method of frequency domain computation is discussed. Selected results from 2D and quasi 3D flow in steady, and unsteady states are presented.作者: ANA 時(shí)間: 2025-3-26 17:16
BEM for the Analysis of Unsteady Aerodynamics of Windmill Rotors in the Presence of Yawal approaches were used to study this problem [2, 3]. Because of this lack of data on the wake geometry, the approaches used in the non-axial flow analysis are typically experimental [4, 5, 6]: a free-wake analysis is included in this paper. The formulation used is closely related to that of Morino and Bharadvaj [8].作者: 白楊 時(shí)間: 2025-3-26 21:21
Time and Frequency Domain Aerodynamics for Flutter of Helicopter Rotors in Hover], although a boundary-element formulation has been used by Kwon [2] for a flutter analysis). The results demonstrate that Loewy’s formulation [3] yields results that are considerably different from those obtained with the more accurate model introduced here.作者: amphibian 時(shí)間: 2025-3-27 01:34 作者: Visual-Field 時(shí)間: 2025-3-27 09:21
Boundary Element Methods for the Navier Stokes Equations is very accurate and cost efficient when applied to two-dimensional, incompressible problems. Research is now being performed to extend the procedure to two-dimensional compressible flows and to three-dimensional incompressible flows. This research is reviewed in this paper.作者: vascular 時(shí)間: 2025-3-27 11:30
Boundary Element-Lagrangian Solution Method for Nonlinear Free Surface Problemse which is constricted in aim at the use of the simplest boundary element, i.e., the constant element. The solution method is applied to several examples on the forced horizontal oscillation of a fluid in containers and generation, propagation, run-up and reflection on a vertical wall of a solitary water wave.作者: SSRIS 時(shí)間: 2025-3-27 15:42
ent features of the BEM have been well documented in the open literature and therefore will not be elaborated here. The BEM research has progressed rapidly, especially in the past decade and continues to evolve worldwide. This Symposium was organized to provide an international forum for presentatio作者: 健談的人 時(shí)間: 2025-3-27 17:55
2 The neutron as an elementary particle,model. The structural model of the elastic blade is a geometrically nonlinear beam model which allows for moderately large deflections. The results are compared with traditional two-dimensional airfoil theory and with experimental data where available.作者: 配偶 時(shí)間: 2025-3-27 22:25
11 Average neutron resonance parameters,ACA23012 are obtained for various angles of attack either with or without boundary layer separation. The emphasis in the following article will be on the explanation of the mathematical model and the presentation of the predicted flow characteristics.作者: 話 時(shí)間: 2025-3-28 02:22
11 Average neutron resonance parameters,d the Stokes equations. The advection solutions can be first obtained by means of both a simple iterative procedure and an interpolation with the cubic spline. By using these solutions, the Stokes equations are solved by the standard boundary element method. This technique is illustrated by several numerical results.作者: 幸福愉悅感 時(shí)間: 2025-3-28 08:36
11 Average neutron resonance parameters,ion of reference velocities and temperatures, volume modeling can often be confined to a small portion of the problem domain, typically near obstacles or walls. The numerical implementation makes use of all of the recent advances in boundary element technology, including higher order elements, adaptive integration, and multi-region capability.作者: BOAST 時(shí)間: 2025-3-28 12:06 作者: 蜈蚣 時(shí)間: 2025-3-28 15:36
A Vortex Method for Predicting Unsteady Flow and Boundary Layer Development Around an AirfoilACA23012 are obtained for various angles of attack either with or without boundary layer separation. The emphasis in the following article will be on the explanation of the mathematical model and the presentation of the predicted flow characteristics.作者: Virtues 時(shí)間: 2025-3-28 19:03
Boundary Element Analysis of Viscous Fluid Flow Problems Using the Time Splitting Methodd the Stokes equations. The advection solutions can be first obtained by means of both a simple iterative procedure and an interpolation with the cubic spline. By using these solutions, the Stokes equations are solved by the standard boundary element method. This technique is illustrated by several numerical results.作者: Neonatal 時(shí)間: 2025-3-29 00:05 作者: engrave 時(shí)間: 2025-3-29 03:34
11 Average neutron resonance parameters,given in Morino and Tseng (1990) for potential flows, in Morino (1990) for viscous flows (potential-vorticity decomposition), and in Piva and Morino (1990) for viscous flows (primitive-variable formulation).作者: comely 時(shí)間: 2025-3-29 10:35
11 Average neutron resonance parameters,-Cole type-difference scheme is used to compute derivatives of density, and shocks are captured automatically. The scheme has been applied to the flow around a rectangular wing at transonic speeds undergoing acceleration motion. The time history of the wing surface pressure distributions has been presented.作者: inconceivable 時(shí)間: 2025-3-29 14:29
A Unified Approach for Potential and Viscous Flows in Fixed-Wing and Rotary-Wing Aerodynamicsgiven in Morino and Tseng (1990) for potential flows, in Morino (1990) for viscous flows (potential-vorticity decomposition), and in Piva and Morino (1990) for viscous flows (primitive-variable formulation).作者: 希望 時(shí)間: 2025-3-29 17:52
Unsteady Three-Dimensional Transonic Flow Computations Using Field Element Method-Cole type-difference scheme is used to compute derivatives of density, and shocks are captured automatically. The scheme has been applied to the flow around a rectangular wing at transonic speeds undergoing acceleration motion. The time history of the wing surface pressure distributions has been presented.作者: Eeg332 時(shí)間: 2025-3-29 23:05 作者: 上漲 時(shí)間: 2025-3-30 00:48
A Boundary Element Model for the Taylor-Couette Instabilityem having a different wavelength of the vortices. At larger values of the Reynolds number a second non-axisymmetric instability modifies the toroidal vortices by means of an azimuthal oscillation which leads to travelling waves. The instability of the basic Couette flow, that was theoretically analy作者: Jingoism 時(shí)間: 2025-3-30 05:41 作者: Cocker 時(shí)間: 2025-3-30 09:12 作者: abnegate 時(shí)間: 2025-3-30 15:37
Conference proceedings 1990devoted to parallel/vector supercomputing with emphasis on mas- sive parallelism. This Symposium was sponsored by United Technologies Research Center (UTRC) , NASA Langley Research Center, and the International Association of Boundary Ele- ment Methods (lAB EM) . We thank the UTRC management for the作者: SEVER 時(shí)間: 2025-3-30 17:42
ssion was devoted to parallel/vector supercomputing with emphasis on mas- sive parallelism. This Symposium was sponsored by United Technologies Research Center (UTRC) , NASA Langley Research Center, and the International Association of Boundary Ele- ment Methods (lAB EM) . We thank the UTRC management for the978-3-642-84240-5978-3-642-84238-2作者: Hirsutism 時(shí)間: 2025-3-30 22:40
A Coupling of BEM and FEM for the Viscous Flow Problem作者: 壓倒 時(shí)間: 2025-3-31 04:57 作者: Rct393 時(shí)間: 2025-3-31 08:17 作者: gorgeous 時(shí)間: 2025-3-31 12:30
https://doi.org/10.1007/978-3-642-84238-2Acoustics; Boundary Elements; Mechanik; Randelemente; Randelementmethode; W?rmeübertragung; aerodynamics; d作者: MURAL 時(shí)間: 2025-3-31 13:48
978-3-642-84240-5Springer-Verlag Berlin Heidelberg 1990作者: NICHE 時(shí)間: 2025-3-31 20:08
Linkage Between Potential and Viscous Flowss flows. This linkage permits the removal of conceptual difficulties and uncertainties resulting from the inviscid fluid idealization of the panel method. Extremely efficient and accurate boundary element methods are established for flows in the absence of significant separated regions.作者: 原諒 時(shí)間: 2025-3-31 23:36 作者: defibrillator 時(shí)間: 2025-4-1 03:10 作者: 大猩猩 時(shí)間: 2025-4-1 07:19
2 The neutron as an elementary particle,vestigate the effects of three-dimensional unsteady aerodynamics on coupled flap-lag-torsion aeroelastic stability using a realistic contracting wake model. The structural model of the elastic blade is a geometrically nonlinear beam model which allows for moderately large deflections. The results ar作者: 減至最低 時(shí)間: 2025-4-1 11:30 作者: Charade 時(shí)間: 2025-4-1 14:22 作者: Pigeon 時(shí)間: 2025-4-1 21:13 作者: upstart 時(shí)間: 2025-4-2 00:49 作者: ITCH 時(shí)間: 2025-4-2 02:58
11 Average neutron resonance parameters,minar and turbulent boundary layers are treated. By using even a rather small computer, reasonable prediction of starting flows around an airfoil of NACA23012 are obtained for various angles of attack either with or without boundary layer separation. The emphasis in the following article will be on 作者: 健談 時(shí)間: 2025-4-2 07:19 作者: incredulity 時(shí)間: 2025-4-2 12:59
11 Average neutron resonance parameters,ential aerodynamics and to introduce an extension of the formulation to compressible viscous flows. For the sake of simplicity, details of the formulation are given only for incompressible flows. For compressible flows, the formulations are only outlined. Also, because of space limitations no numeri
