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A goal of this verification example is to analyze the fluid flow around the glider. The task is to determine the drag coefficient and lift coefficient with respect to the angle of attack. These coefficients can be also drawn into the graph of drag polar. From the velocity field can be also determined the limit angle for laminar fluid flow around the wing profile. The available 3D CAD model (STL file) is used in RWIND 2.
Model Used in
Verification Example 0307 | 1
You can download this structural model to use it for training purposes or for your projects. However, we do not assume any guarantee or liability for the accuracy or completeness of the model.