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检索条件"主题词=solution algorithm"
198 条 记 录,以下是101-110 订阅
排序:
Unstructured method for flows past bodies in general three-dimensional relative motion
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AIAA JOURNAL 2001年 第2期39卷 219-224页
作者: Singh, KP Baysal, O Old Dominion Univ Dept Aerosp Engn Norfolk VA 23529 USA Old Dominion Univ Coll Engn & Technol Norfolk VA 23529 USA
A three-dimensional methodology was developed for unsteady flows past bodies that are in relative motion and where the trajectory of the motion was determined from the instantaneous aerodynamic field. This method coup... 详细信息
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Sensitivity of mixed subsonic-supersonic turbulent mixing layers
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JOURNAL OF PROPULSION AND POWER 2001年 第4期17卷 823-835页
作者: Cottrell, DC Plesniak, MW Purdue Univ Sch Mech Engn Maurice J Zucrow Labs W Lafayette IN 47907 USA
Numerical predictions of compressible turbulent mixing layers have been performed for convective Mach numbers up to 0.7 (M-C less than or equal to0.7), This flow is particularly challenging to compute because the mixi... 详细信息
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Unified formulation for compressible-incompressible flow simulation with mesh adaptation
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AIAA JOURNAL 2001年 第12期39卷 2425-2427页
作者: Turgeon, É Pelletier, D Ecole Polytech Dept Genie Mech Montreal PQ H3C 3A7 Canada
Proposes a pressure-based formulation capable of handling compressible and incompressible flows. Temperature dependence of air properties; Role of absolute pressure and pressure differences; Application of a standard ... 详细信息
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Unstructured grid arbitrarily shaped element method for fluid flow simulation
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AIAA JOURNAL 2000年 第12期38卷 2246-2252页
作者: Lai, YG Univ Iowa Iowa Inst Hydraul Res Iowa City IA 52242 USA
A three-dimensional unstructured grid arbitrarily shaped element method is developed for solving the Navier-Stokes equations. The proposed method is generally applicable to arbitrarily shaped elements and, thus, offer... 详细信息
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Attitude feedback control: Unconstrained and nonholonomic constrained cases
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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2000年 第4期23卷 657-664页
作者: Aicardi, M Cannata, G Casalino, G Univ Genoa Dept Commun Comp & Syst Sci DIST I-16145 Genoa Italy
The problem is considered of asymptotically driving, the attitude of a spacecraft via feedback control. First, a simple feedback control structure based on the measure of the equivalent angle axis is determined for a ... 详细信息
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Structural dynamics and quasistatic aeroelastic equations of motion
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JOURNAL OF AIRCRAFT 2000年 第3期37卷 538-542页
作者: Dykman, JR Rodden, WP Boeing Co Long Beach CA 90807 USA
Presents information on a study which focused on the structural dynamics and the quasistatic aeroelastic equations of motions of a flight vehicle. Residualization of the aeroelastic equations of motion; Coefficients f... 详细信息
来源: 评论
Modification of a helicopter inverse simulation to include an enhanced rotor model
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JOURNAL OF AIRCRAFT 2000年 第3期37卷 536-538页
作者: Doyle, SA Thomson, DG Univ Glasgow Dept Aerosp Engn Glasgow G12 8QQ Lanark Scotland
An individual blade rotor model has been developed at the University of Glasgow by Rutherford and Thomson (1997) for use in helicopter inverse simulation. In the context of helicopter flight dynamics, an inverse simul... 详细信息
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Numerical optimization of the suction distribution for laminar flow control
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AIAA JOURNAL 2000年 第2期38卷 370-372页
作者: Tutty, OR Hackenberg, P Nelson, PA Univ Southampton Sch Engn Sci Southampton SO17 1BJ Hants England Univ Southampton Inst Sound & Vibrat Res Southampton SO17 1BJ Hants England
Deals with a study on aerodynamics which developed an algorithm to solve the numerical optimization problem in suction distribution for laminar flow control. Flat plate configuration; Plate with pressure gradient; Con... 详细信息
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Numerical investigation of installation effects in turbofan engines
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JOURNAL OF PROPULSION AND POWER 2000年 第4期16卷 697-704页
作者: Joo, WC Yonsei Univ Dept Mech Engn Seoul 120749 South Korea
One of the important issues in the assessment of intake/engine compatibility in civil turbofan engines is the prediction of the coupling effects between the intake and the engine. An actuator-disk model has been appli... 详细信息
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Two-timescale-integration method for inverse simulation
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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1999年 第3期22卷 395-401页
作者: Avanzini, G de Matteis, G de Socio, LM Politecn Torino Dept Aerosp Engn I-10129 Turin Italy Univ Roma La Sapienza Dept Mech & Aeronaut I-00184 Rome Italy
The integration method is extensively applied in the inverse simulation of aircraft motion where control inputs are determined once a maneuver or flight task is assigned. In many circumstances the presence of multiple... 详细信息
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