Обтекание крылового профиля NACA 0012

NACA 0012
NACA 0012
0.745).
0.3
(
(
) NACA 0012.
)
*
)
(“Euler
Solutions for A Medium Range Cargo Aircraft” Middle East Technical University Aeronautical
Engineering Department by Cengizhan Bahar “NACA 0012. Oscillating and Transient Pitching,”
Data Set 3 in AGARD--R--702, Compendium of Unsteady Aerodynamic Measurements, Aug. 1982
by R. H. Landon).
(
S
1
2
3
4
0.3
0.3
0.3
0.745
),
Y:
VW
*
Re
1.86e+7
1.86e+7
1.86e+7
5.28E+11
VW
S ) -[
*
.
\
,
X
YX
3.59
8
12
3.35
,
Y
!
]
^
Y
._
Y *
V
,
`
Y *
)
3°
Y
12°.
Y
\
Y
Y
0.1 .
( )
)^ 3 .
Y
b
X
.
V
.
4
2
1
3
1) S
\ 1 –
(Inlet/Outlet ( 2) S
\ 2–
Outlet (>
\ 3 –
3) S
(Wall (>
4) S
\ 4 (
(Symmetry (>
*
(
/
<))*.
?
)
)
Normal
) Y
velocity with
)V V
Density
Zero Pressure/Outlet (;
Wall, logarithm law (>
),
) Wall with Slip (>
VW
\
)
/
,
Z) –
V
)V
(;
?E
E
,
)
)
.
)
.
113 85 1,
W
)).
)).
H
h
p=0 (Free
- )).
,
Re
H E
I
h
)
C
)
Cy =
Fy
V
2
p
=
p
=
2
c b
)
p
V 2
2
1
C p dx ,
c
*
\
Fy –
i
i
*
\
Y
,b–
Y
Z.
1.5
1.0
-Cp
0.5
0.0
-0.5
-1.0
-1.5
0.0
0.2
0.4
x/c
k
m *
\
0.6
0.8
FlowVision
)
M=0.3, =3.59°.
1.0
1.4
1.2
1.0
Cy
0.8
0.6
0.4
0.2
0.0
-0.2
-0.4
-2
0
2
4
6
8
10
k
FlowVision (
FlowVision (
m *
12
14
)
)
\
M=0.3.
1.5
1.0
-Cp
0.5
0.0
-0.5
-1.0
-1.5
0.0
0.2
0.4
x/c
0.6
0.8
FlowVision
m *
\
)
M=0.745, =3.35°.
1.0