Detail of the computational mesh at a flap angle of 
= 35o
To capture the geometry in the case of a moving flap the numerical grid needs to be distortable. Starting with a basic mesh at a low flap angle, the mesh around the upward-moving flap is deformed with a method based on an analogy to structure mechanics. If neccessary, a biharmonic smoothing algorithm is applied to improve the mesh quality.
Lift coefficient over angle of attack for the clean HQ17 airfoil
predicted by different turbulence models (Re = 106)
Numerical investigations of the clean airfoil show that the flow becomes unsteady at high angles of attack with a vortex street developing.
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Last modified: Wed Jul 26 19:07:26 CEST 2000
