Comparing different CFD software with NACA 2412 airfoil
نویسندگان
چکیده
منابع مشابه
Verification of a CFD solver in near ground effect for aerodynamic behavior of airfoil NACA 0015
Numerical investigation was performed on NACA 0015 which is a symmetric airfoil. Pressure distribution and then lift and drag forces are verified. Changing of ground clearance was a considerable point. Also the angle of attack was changed from 0° to 10°. Pressure coefficient reaches its higher amounts on the wing lower surface when the ground clearance diminishes. Increment of the angle of atta...
متن کاملCFD study on NACA 4415 airfoil implementing spherical and sinusoidal Tubercle Leading Edge
The Humpback whale tubercles have been studied for more than a decade. Tubercle Leading Edge (TLE) effectively reduces the separation bubble size and helps in delaying stall. They are very effective in case of low Reynolds number flows. The current Computational Fluid Dynamics (CFD) study is on NACA 4415 airfoil, at a Reynolds number 120,000. Two TLE shapes are tested on NACA 4415 airfoil. The ...
متن کاملCorrection: CFD study on NACA 4415 airfoil implementing spherical and sinusoidal Tubercle Leading Edge
[This corrects the article DOI: 10.1371/journal.pone.0183456.].
متن کاملAnalysis of wings using Airfoil NACA 4412 at different angle of attack
The purpose of this paper is to analysis the basic aerodynamic theory of wings and the provide an introduction to wind tunnel testing. This is followed by the result from the wind tunnel testing of a NACA4412 and the analysis of the data. Lift increase at the angle of attack increase at certain point and at this point it become maximum. After that if the angle of attack is increased by further,...
متن کاملAerodynamic Performance Enhancement of a NACA 66-206 Airfoil Using Supersonic Channel Airfoil Design
Supersonic channel airfoil design techniques have been shown to significantly reduce drag in high-speed flows over diamond shaped airfoils by Ruffin and colleagues. The effect of applying these techniques to a NACA 66-206 airfoil is presented. The design domain entails channel heights of 8-16.6% thickness-to-chord and speeds from Mach 1.5-3.0. Numerical simulations show an increase in the lift-...
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ژورنال
عنوان ژورنال: Progress in Agricultural Engineering Sciences
سال: 2020
ISSN: 1786-335X,1787-0321
DOI: 10.1556/446.2020.00004