Themes > Science > Physics > Fluid Dynamics > Flying the flag for fluid dynamics > Aerodynamics > Selected Topics of Model Aerodynamics > Designing an Airfoil > Comparison between Theory and Experiment

When comparing experimental and theoretical results, you should bear in mind, that neither wind tunnels nor computers perfectly represent the reality. As discussed above, wind tunnels have shortcomings like fixed walls, turbulence, noise and model quality, whereas theory is always based on a mathematical model of the real world - assuming this and neglecting that. A typical comparison is given below; at lower Reynolds numbers the discrepancies can be even larger.

Comparison Experiment <-> Theory
Comparison of theoretical with experimental results.

The figure above shows a typical comparison between both theoretical analysis methods and experimental results at low Reynolds numbers. The experiment shows the strong influence of a laminar separation bubble, which roughly doubles the drag coefficient. The Eppler code cannot cope with laminar separation bubbles, but issues a warning for all the calculated data points, saying that there might be a separation bubble. Drela's XFOIL takes the laminar separation bubble into account, but under predicts the drag. Thus both methods cannot predict the drag values at Reynolds numbers below 200'000 if laminar separation occurs, but hint the user that something might be happening.
My experiences with XFOIL indicate, that it tends to shift the polars to higher lift coefficients and that the simple panel method (in conjunction with the spline method) has some problems with leading edges, which often results in jaggy velocity distributions even for perfectly smooth airfoils.

It is very, very difficult to make a fair comparison of airfoils at low Reynolds numbers. On the one hand, numerical methods have serious shortcomings, but can be used to judge airfoils under comparable conditions. On the other hand, experiments are not only difficult and time consuming, but can also yield very different results even in the same wind tunnel, due to the three dimensional nature of laminar separation bubbles and spanwise variations in lift and drag. These variations can be much bigger than the differences between different airfoils, thus making a comparison of two dimensional polars, as measured by a single wake rake questionable.


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