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CL | Cd | |
---|---|---|
FLUENT | 0.647 | 0.00249 |
Experiment | 0.6 | 0.007 |
% Dif | 7.8% | 64% |
CL | Cd | |
---|---|---|
FLUENT Fine Mesh | 0.649 | 0.00137 |
Experiment | 0.6 | 0.007 |
Theory | 0 |
Though further validation steps are still needed before we can come up with a model that will accurately represent the physical flow, this simple tutorial demonstrates the use of reasonable assumption and approximation in obtaining understanding of physical flow properties around an airfoil.
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