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Description: 基于James格式的CFD程序,计算NACA0012翼型流场和升力阻力系数.网格由Fluent提供的Gmbit生成,计算结果可以通过Tecplot观看-James formats based on the CFD program to calculate the flow field and the NACA0012 airfoil lift drag coefficient. Fluent grid provided by the Gmbit generated, calculated results can Tecplot Views
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Size: 876544 |
Author: 凌维安 |
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Description: NACA0012翼型流场计算。结构化网格，AUSM格式。-NACA0012 airfoil flow field
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Size: 598016 |
Author: newanda |
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Description: this code can be used to develop C-type grid generaton for naca 0012 airfoil. by import the airfoil dots with manner of the code, you can develop c_type grid for any airfoil.
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Size: 3072 |
Author: kiarash |
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Description: list of lift coefficeint and drag coefficient for naca 0012 at different reynolds No.
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Size: 15360 |
Author: kiarash |
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Description: validation paper for Laminar viscous Compressible flow, Over Naca 0012- validation paper for Laminar viscous Compressible flow, Over Naca 0012
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Size: 797696 |
Author: kiarash |
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Description: Drag prediction for Naca 0012 by use of different source codes and Compare with Experiment results.
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Size: 732160 |
Author: kiarash |
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Description: In this book , a low-speed airfoil over the NACA 0012 airfoil at 2° and 14° attack angles with
the given inlet velocity of 0.25 m/s, was modeled and computational fluid dynamic (CFD)
analysis were performed using FLUENT in ANSYS. The Reynolds number based on the chord is
roughly 𝑅 𝑒 = 2.88 × 106. The flow was modeled as incompressible and inviscid. All setup and
procedures were done by following the steps provided Cornel University website. Though, mesh
independence was achieved for 2° attack angle, for 14° attack angle which is more than the stall angle, mesh independence was not achieved. Lift and drag coefficient increases as the number of mesh element or the attack angle increases.-In this book , a low-speed airfoil over the NACA 0012 airfoil at 2° and 14° attack angles with
the given inlet velocity of 0.25 m/s, was modeled and computational fluid dynamic (CFD)
analysis were performed using FLUENT in ANSYS. The Reynolds number based on the chord is
roughly 𝑅 𝑒 = 2.88 × 106. The flow was modeled as incompressible and inviscid. All setup and
procedures were done by following the steps provided Cornel University website. Though, mesh
independence was achieved for 2° attack angle, for 14° attack angle which is more than the stall angle, mesh independence was not achieved. Lift and drag coefficient increases as the number of mesh element or the attack angle increases.
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Size: 3686400 |
Author: ahmed |
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