HeldenMesh ケーススタディ
HeldenMeshによるケーススタディ一覧です。
航空機 ＜1＞
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2nd High Lift Prediction Workshop Common Research Model
Number of Nodes: 15,511,954
Number of Prisms: 13,537,326
Number of Pyramids: 219,258
Number of Tets: 49,379,944
Number of Total Cells: 63,136,528
Time: 550.85 s
実行環境: Ubuntu / Hyper-V / Intel(R) Core(TM) i7-1260P 2.10 GHz / 8 並列 / RAM 32GB
航空機 ＜2＞
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P-51 Mustang
Number of Prisms: 5,491,553
Number of Pyramids: 87,369
Number of Tets: 20,754,950
Number of Total Cells: 26,333,871
Time: 121.36 s
実行環境: Ubuntu / Hyper-V / Intel(R) Core(TM) i7-1260P 2.10 GHz / 8 並列 / RAM 32GB
航空機 ＜3＞
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NASA X-59 QueSST
Number of Nodes: 7,716,144
Number of Prisms: 5,287,404
Number of Pyramids: 40,202
Number of Tets: 28,709,528
Number of Total Cells: 34,037,136
Time: 334.38 s
実行環境: Ubuntu / Hyper-V / Intel(R) Core(TM) i7-1260P 2.10 GHz / 8 並列 / RAM 32GB
自動車部品
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インテークマニホールド
Number of Nodes: 437,699
Number of Prisms: 573,288
Number of Pyramids: 12,719
Number of Tets: 761,344
Number of Total Cells: 1,347,350
Time: 11.60 s
実行環境: Ubuntu / Hyper-V / Intel(R) Core(TM) i7-1260P 2.10 GHz / 8 並列 / RAM 32GB
ターボ機械
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ガスタービン冷却翼
Number of Nodes: 1,049,736
Number of Tets: 5,691,374
Number of Total Cells: 5,691,374
実行環境: Ubuntu / Hyper-V / Intel(R) Core(TM) i7-1260P 2.10 GHz / 8 並列 / RAM 32GB
空力とCFDの関連文献
- Hybrid Wing Body Performance Validation at the National Transonic Facility（AIAA 2017-0099)
- Powered Low Speed Testing of the Hybrid Wing Body（AIAA 2017-0100)
- Transonic Semispan Aerodynamic Testing of the Hybrid Wing Body（AIAA 2015-0098)
- Integrated Aerodynamic Benefits of Distributed Propulsion（AIAA 2015-1500)
- Design of a Hybrid Wing Body for Fuel Efficient Air Mobility Operations（AIAA-2014-1285)
- Over Wing Nacelle Installations for Improved Energy Efficiency（AIAA 2013-2920)
- Design and Transonic Wind Tunnel Testing of a Cruise Efficient STOL Transport（AIAA 2013-1100)
- Low Speed Powered Lift Testing of a Transonic Cruise Efficient STOL Military Transport（AIAA 2013-1099)
- Powered Lift CFD Predictions of a Transonic Cruising STOL Military Transport（AIAA 2013-1098)
- Reduction of Aft Fuselage Drag on the C-130 Using Microvanes（AIAA 2013-0105)
- "Using Knowledge-based Optimization with TetrUSS,” Presented at USM3D Users Group Meeting, October 2008.
- Numerical Simulation of the Splashdown Problem（AIAA 2007-0373)
- Numerical Study of Axi-Symmetric Bodies Falling Into Water（AIAA 2007-0342)
- Application of the Unstructured Chimera Method for Rapid Weapons Trajectory Simulations（AIAA 2007-75)
- Computational Simulation of an Unmanned Aerial Vehicle Impacting Water（AIAA 2007-70)
- The Application of CFD for the Aerodynamic Development of the C-5M Galaxy（AIAA 2006-0856)
- Characterization of Wing Icing by its Fractal Dimension（AIAA Region V Student Conference 2005)
- Algorithm Development of a 'Galactic Positioning System（AIAA Region V Student Conference 2005)
- Aerodynamic Development of a Refueling Pod for Tanker Aircraft（AIAA 2002-2805)
- Validation of Unstructured Grid Euler/Navier-Stokes Code on Full Aircraft with Propellers（AIAA 2001-1003)
- Advanced Pylon Design using Computational Fluid Dynamics（Memorandum C1-1XG-FP-95-241)
- Spatial and Temporal Adaptive Procedures for the Unsteady Aerodynamic Analysis of Airfoils using Unstructured Meshes（AIAA 92-2694)