Flow
around a NACA 0012 airfoil
Submission
of results
For each test case
seven files should be submitted with the names:
description_CASExy_setz.txt
conv_data_cd_CASExy_setz.dat
conv_surface_cflo_CASExy_setz.dat
conv_surface_cplo_CASExy_setz.dat
conv_surface_cfup_CASExy_setz.dat
conv_surface_cpup_CASExy_setz.dat
field_points_r1.000_CASExy_setz.dat
field_points_r2.000_CASExy_setz.dat
CASExy_setz
identifies the set of data used to obtain the uncertainties, where
|
x |
IV, V or VI |
|
y |
a, b or c |
|
z |
1, 2, 3, 4, 5, 6 |
|
CASE IV |
|
a |
Spalart & Allmaras |
|
CASE V |
|
b |
k-w SST |
|
CASE VI |
|
c |
|
For example,
CASEVb_set3 corresponds to the grids with the third smallest size of the
near-wall cells (set3) for 
(CASEV) and the k-w SST two-equation
turbulence model (b).
File description_CASExy_setz.txt should indicate the
technique applied for the estimation of the numerical uncertainty and the grids
that provided the data for the uncertainty estimation.
File conv_data_cd_CASExy_setz.dat should contain 2
lines with 5 columns. First line should be for 
and second line for 
.
Column 1 ― Grid
refinement ratio 
.
Column 2 ―
Absolute value of the estimated numerical uncertainty for the friction drag coefficient 
.
Column 3 ―
Absolute value of the estimated numerical uncertainty for the pressure drag coefficient 
.
Column 4 ―
Absolute value of the estimated numerical uncertainty for the friction lift coefficient 
.
Column 5 ―
Absolute value of the estimated numerical uncertainty for the pressure lift coefficient 
.
File conv_surface_cflo_CASExy_setz.dat should contain 2
lines with 20 columns. First line should be for and second line for 
.
Column 1 corresponds
to the grid refinement ratio and columns to 2 to 20
to the absolute value of the estimated numerical uncertainty of the skin
friction coefficient 
at the 19 selected
locations of the lower surface of
the airfoil given in the table below.
File conv_surface_cplo_CASExy_setz.dat should contain 2
lines with 20 columns. First line should be for and second line for .
Column 1 corresponds
to the grid refinement ratio and columns to 2 to 20
to the absolute value of the estimated numerical uncertainty of the pressure
coefficient 
at the 19 selected
locations of the lower surface of
the airfoil given in the table below.
|
Column |
|
Column |
|
Column |
|
Column |
|
|
2 |
0.025 |
7 |
0.275 |
12 |
0.525 |
17 |
0.775 |
|
3 |
0.075 |
8 |
0.325 |
13 |
0.575 |
18 |
0.825 |
|
4 |
0.125 |
9 |
0.375 |
14 |
0.625 |
19 |
0.875 |
|
5 |
0.175 |
10 |
0.425 |
15 |
0.675 |
20 |
0.925 |
|
6 |
0.225 |
11 |
0.475 |
16 |
0.725 |
|
|
Selected locations
for the lower surface of the airfoil
(
is aligned with the
chord of the airfoil)
File conv_surface_cfup_CASExy_setz.dat should contain 2 lines
with 20 columns. First line should be for and second line for .
Column 1 corresponds
to the grid refinement ratio and columns to 2 to 20
to the absolute value of the estimated numerical uncertainty of the skin
friction coefficient at the 19 selected
locations of the upper surface of
the airfoil given in the table below.
File conv_surface_cpup_CASExy_setz.dat should contain 2 lines
with 20 columns. First line should be for and second line for .
Column 1 corresponds
to the grid refinement ratio and columns to 2 to 20
to the absolute value of the estimated numerical uncertainty of the pressure
coefficient at the 19 selected
locations of the upper surface of
the airfoil given in the table below.
|
Column |
|
Column |
|
Column |
|
Column |
|
|
2 |
0.05 |
7 |
0.3 |
12 |
0.55 |
17 |
0.8 |
|
3 |
0.1 |
8 |
0.35 |
13 |
0.6 |
18 |
0.85 |
|
4 |
0.15 |
9 |
0.4 |
14 |
0.65 |
19 |
0.9 |
|
5 |
0.2 |
10 |
0.45 |
15 |
0.7 |
20 |
0.95 |
|
6 |
0.25 |
11 |
0.5 |
16 |
0.75 |
|
|
Selected locations
for the upper surface of the airfoil
( is aligned with the
chord of the airfoil)
Files field_points_r1.000_CASExy_setz.dat () and field_points_r2.000_CASExy_setz.dat () should contain 166 lines with the first line indicating the
grid refinement ratio 
and the total number of points available
(165). The next 165 lines should contain 5 colums.
Column 1 ―
Horizontal coordinate 
(with 
aligned with the
incoming flow).
Column 2 ―
Vertical coordinate 
(with 
perpendicular to the
incoming flow).
Column 3 ― Absolute
value of the estimated numerical uncertainty of the horizontal velocity component 
.
Column 4 ―
Absolute value of the estimated numerical uncertainty of the vertical velocity component 
.
Column 5 ―
Absolute value of the estimated numerical uncertainty of the kinematic eddy-viscosity 
.