CFD Analysis of Blunt Trailing Edge Airfoils Obtained with Several ...
CFD Analysis of Blunt Trailing Edge Airfoils Obtained with Several ...
CFD Analysis of Blunt Trailing Edge Airfoils Obtained with Several ...
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18 <br />
<br />
<br />
l d <br />
lift-drag ratio (L/D) and quarter chord moment<br />
coefficient (C m ) are calculated for each even angle <strong>of</strong><br />
<br />
The output parameters derived are: angle <strong>of</strong> zero lift<br />
lo l max -<br />
l max <br />
(C d min max <br />
max <br />
This experiment allows us to recognize the way the<br />
effects <strong>of</strong> main geometric parameters interact <strong>with</strong><br />
the modification parameters by analyzing the mean<br />
<br />
Although this does not permit us to derive equations<br />
<br />
<br />
NACA 4421 STUDY<br />
-<br />
<br />
airfoil was modified using the cutting <strong>of</strong>f (R) and<br />
<br />
<br />
<br />
<br />
<br />
<br />
A complete detailed analysis <strong>of</strong> a single airfoil is required<br />
in order to quantify the effect <strong>of</strong> the modification<br />
and to fully understand its effects on aerody-<br />
<br />
following output variables are studied: The lift curve<br />
slope (m = dC l lo mum<br />
lift coefficient (C l max <br />
l max max -<br />
max nimum<br />
drag coefficient (C d min <br />
moment coefficient at zero lift (C mo <br />
RESULTS<br />
In this section the results from both studies are pre-<br />
sults<br />
are shown in terms <strong>of</strong> the mean <strong>of</strong> the output<br />
<br />
<br />
<br />
FOUR-DIGIT NACA AIRFOIL FAMILY RESULTS<br />
(FIGURES 5, 6)<br />
The airfoil modification effect on stall region is<br />
<br />
higher maximum lift coefficient than the cutting <strong>of</strong>f<br />
ness<br />
increases the maximum lift coefficient and the<br />
-
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