CFD Analysis of Blunt Trailing Edge Airfoils Obtained with Several ...

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técnica #33 revista de ingeniería 21 appear as the trailing edge thickness has an overall opposite effect to mean camber and airfoil thick- - The added thickness method produces airfoils that tion and chord line orientation; consequently the allows separating the effect of the modification pa- llowing effects are recognized: - - - for modified airfoils with a trailing edge thickness of
22 6 ) 6 ) The lift coefficient curve is larger for the added thickness method over the entire angle of attack - The drag coefficient increase is smaller for the cutting off method than for the added thickness base drag caused by the pressure distribution in the crepancy in the drag increase between the methods is caused by the smaller surface drag produced by The zero lift moment coefficient does not vary for CONCLUSIONS Two different blunt trailing edge airfoil modifica- cutting off method was typically considered in the namic performance of the cutting off method have been reported since this method leads to a change in added thickness method has been formerly pointed out as a method that allows the full differentiation between the effects of airfoil geometric parameters The added thickness method proved to have better lift enhancement than the cutting off method because it does not reduce the mean camber and does not
Page 1 and 2: 14 técnica CFD Analysis of Blunt T
Page 3 and 4: 16 METHODS COMPUTATIONAL MODEL A tw
Page 5 and 6: 18 l d lift-dr
Page 7: 20 Figure 7. Trailing Edge Thicknes
Page 11: 24 New Section Shapes for Wind Tur

CFD Analysis of Blunt Trailing Edge Airfoils Obtained with Several ...

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