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6.The computer model (2/2)
f.
The calculation grid for the front wing was constructed to
include 1764 cells. Fig. 4 shows the grid of the front wing in
ground effect. Fig. 5, which has 10,968 cells, shows the grid
pattern for the back wing.
g. A grid independency test was performed on the front airfoil to
determine a suitable mesh size for the problem.
h. Three nodal densities were chosen for the runs, i.e. 2208, 4416
and 8832 nodes. Fig. 6 and Table 1 present results to validate
the choice of grid density. Fig. 6
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7.Results and discussions (1/5)
a.
b.
The results of the computer simulations were complied and
plotted graphically.
Front wing and rear wing
Ps：
 the non-dimensional u/U
 u is the horizontal velocity near the wing .
 U is the frees tream horizontal velocity used at the entry to the
solution field.
 x is the horizontal dimensional variable starting from the front tip of
the wing,
 c is the chordal length of the wing horizontally from the upstream
tip to the wing’s tail.
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