ChaldExals |
September 20, 2022 15:01 |
Validity of the Drag Force acting on a Wing
2 Attachment(s)
Hi Everyone,
I ran a CFD analysis on NACA 0006 wing at 0 angle of attack. The root length,tip length and span of the wing is 10cm,8cm,10cm respectively.The freestream velocity is 300 m/s and pressure is 1 atm (sea level conditions). When the analysis is completed the drag acting on the wing is 5N which corresponds to a drag coefficient of 0,005. I am new to CFD but this number seemed so small. Can this be correct? For further information: in the mesh part, I have a minimum orthogonal quality of 0.0138,maximum skewness of 0.95 and maximum aspect ratio of 792 (I checked orthogonal quality and aspect ratio from Fluent). The first layer thickness is 2.5e-6m. I have 15 number of layers with a growth rate of 1.2. In the setup part I converted the mesh to polyhedral mesh. I used density-based solver,ideal gas model and SST k-w turbulence model for air. I also share the mesh and mach number contour I get. Thank you in advance.
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