duwind, delft university wind energy institute 1 an overview of naca 6-digit airfoil series...
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1DUWIND, Delft University Wind Energy Institute
An overview of NACA 6-digit airfoil series characteristics with
reference to airfoils for large wind turbine
Nando Timmer
DUWINDDelft University Wind Energy Institute
The Netherlands
2DUWIND, Delft University Wind Energy Institute
Outline
• Introduction• Measurements in LTPT• Comparison with RFOIL calculations• (Maximum) lift• Drag
• Roughness effects• Conclusions
3DUWIND, Delft University Wind Energy Institute
Introduction
• Large machines have blades performing at Reynolds numbers up to 9 to 10 million
• Many dedicated wt airfoils have not been tested at these Re-numbers
• Testing at these Re-numbers is relatively expensive
• If blade designers do not want to spend this amount of money they have to rely on the predictive value of codes like XFOIL and/or CFD
4DUWIND, Delft University Wind Energy Institute
Introduction (cntd)
• NACA airfoils were tested in the Langley LTPT up to Re=9x106 and can be used to verify the predictions.
• Main question in this presentation is:
• How good are these data anyway and how well can we predict them with RFOIL.(as a typical example we investigate the 18% thick airfoil from the NACA 63 and 64 series)
5DUWIND, Delft University Wind Energy Institute
LTPT measurements
• Test section 3x7.5 feet (0.914 m x 2.29 m)• Model chord 2 feet (0.61 m)• Maximum velocity at atmospheric pressure is
130 m/s• Maximum Mach number during the tests was
0.17• Models were made of laminated mahogany• Lift from the pressure reaction on the walls
(over a length of 13 feet – 3.96 m), drag from a wake rake.
• Basic wind tunnel wall corrections were applied
6DUWIND, Delft University Wind Energy Institute
RFOIL
• Basically XFOIL• Improvement of the numerical stability by using
the Schlichting velocity profiles for the turbulent boundary layer instead of Swafford’s
• the shear lag coefficient in Green’s lag entrainment equation of the turbulent boundary layer model was adjusted
• Deviation from the equilibrium flow was coupled to the shape factor of the boundary layer
7DUWIND, Delft University Wind Energy Institute
Lift
8DUWIND, Delft University Wind Energy Institute
Re = 3.0x106
-1.0
-0.5
0.0
0.5
1.0
1.5
0.000 0.008 0.016 0.024cd
cl
-1.0
-0.5
0.0
0.5
1.0
1.5
-10 0 10 20a (o)
cl
NACA 63-618
NACA 63-418
NACA 63-218
NACA 63-018
9DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re = 6.0x106
-1.0
-0.5
0.0
0.5
1.0
1.5
0.000 0.008 0.016 0.024cd
cl
-1.0
-0.5
0.0
0.5
1.0
1.5
-10 0 10 20a (o)
cl
64-018
64-218
64-418
64-618
10DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re = 9.0x106
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
0.000 0.008 0.016 0.024cd
cl
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
-10 0 10 20a (o)
cl
64-018
64-218
64-418
64-618
11DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re=6x106
-5
-4
-3
-2
-1
0
1
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient, Cl,i
Ze
ro-l
ift a
ng
le (d
eg
ree
s)
LTPT
12DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re=6x106
-5
-4
-3
-2
-1
0
1
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient, Cl,i
Ze
ro-l
ift a
ng
le (d
eg
ree
s)
Inviscid
RFOIL
LTPT
13DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re=6x106
-5
-4
-3
-2
-1
0
1
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient, Cl,i
Ze
ro-l
ift a
ng
le (d
eg
ree
s)
Inviscid
RFOIL
LTPT
Ref. 5
14DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re=6x106
-5
-4
-3
-2
-1
0
1
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient, Cl,i
Ze
ro-l
ift a
ng
le (d
eg
ree
s)
Inviscid
RFOIL
LTPT
Ref. 5
0.4
15DUWIND, Delft University Wind Energy Institute
NACA 64-618
Re = 6.0x106
-1.2
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
0.000 0.005 0.010 0.015 0.020
cd
cl
-1.2
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
-20 -15 -10 -5 0 5 10 15 20
a (o)
cl
RFOIL
LTPT-0.4 degr.
16DUWIND, Delft University Wind Energy Institute
NACA 64-618
Re = 6.0x106
-1.2
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
0.000 0.005 0.010 0.015 0.020
cd
cl
-1.2
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
-20 -15 -10 -5 0 5 10 15 20
a (o)
cl
LM
RFOIL
LTPT-0.4 degr.
17DUWIND, Delft University Wind Energy Institute
NACA 643-618
Re = 9.0x106
-0.5
0.0
0.5
1.0
1.5
2.0
0.000 0.008 0.016 0.024cd
cl
-0.5
0.0
0.5
1.0
1.5
2.0
-10 0 10 20 30a (o)
cl
NACA LTPT
XFOIL v6.97
RFOIL v2003.1
18DUWIND, Delft University Wind Energy Institute
NACA 643-018
Re = 6.0x106
0.0
0.5
1.0
1.5
0.000 0.008 0.016 0.024cd
cl
0.0
0.5
1.0
1.5
0 8 16 24a (o)
cl
RFOIL
positive angles
negative angles
19DUWIND, Delft University Wind Energy Institute
1.3
1.4
1.5
1.6
1.7
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient
Max
imu
m li
ft c
oef
fici
ent
NACA Re=6x10E6
RFOIL Re=6x10E6
negative angles
positive angles
NACA 64-x18
3.5%
20DUWIND, Delft University Wind Energy Institute
1.3
1.4
1.5
1.6
1.7
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient
Max
imu
m li
ft c
oef
fici
ent
NACA Re=9x10E6
RFOIL Re=9x10E6
NACA 64-x18
6.5%
21DUWIND, Delft University Wind Energy Institute
-1.0
-0.5
0.0
0.5
1.0
1.5
-10.0 0.0 10.0 20.0
a (degr.)
cl
Stuttgart
LTPT
RFOIL
NACA 63-418
-1.5
-1.0
-0.5
0.0
0.5
1.0
1.5
-20.0 -10.0 0.0 10.0 20.0a (degr.)
cl
Stuttgart
LTPT
RFOIL
NACA 63-018
-1.0
-0.5
0.0
0.5
1.0
1.5
-10.0 0.0 10.0 20.0
a (degr.)
cl
LTPT
Stuttgart
RFOIL
NACA 63-421
22DUWIND, Delft University Wind Energy Institute
DU 96-W-180
Re = 3.0x106
-1.0
-0.5
0.0
0.5
1.0
1.5
0.00 0.01 0.02 0.03cd
cL
-1.0
-0.5
0.0
0.5
1.0
1.5
-10 0 10 20a (o)
cL
Delft
Stuttgart
RFOIL
23DUWIND, Delft University Wind Energy Institute
1.0
1.2
1.4
1.6
1.8
0 2 4 6 8 10 12Rex10-6
Cl,max
KKK, M=0.1
KKK, M=0.2Du 97-W-300Mod
Base airfoil, Delft
RFOIL, n=9
RFOIL, n=5
24DUWIND, Delft University Wind Energy Institute
Chord (m)
Span (m)
C/S
LM .90 1.35 1.5
LTPT .61 .914 1.5
Test section top view
wall
Separation line
chord
A B C
span
-0.5
0.0
0.5
1.0
1.5
2.0
-10 -5 0 5 10 15 20 25
Wall pressures
Model pressures C
Model pressures B
Model pressures A
LM wind tunnel test setup
25DUWIND, Delft University Wind Energy Institute
T.E L.E
Stall cells
Pressure orifices
26DUWIND, Delft University Wind Energy Institute
NLF(1)-0416
Re = 6.0x106
-0.5
0.0
0.5
1.0
1.5
2.0
0.00 0.01 0.02 0.03cd
cL
-0.5
0.0
0.5
1.0
1.5
2.0
-10 0 10 20a (o)
cL
RFOIL
LTPT
Lift from model pressures
27DUWIND, Delft University Wind Energy Institute
Drag
28DUWIND, Delft University Wind Energy Institute
NACA 643-618
Re = 9.0x106
-0.5
0.0
0.5
1.0
1.5
0.000 0.008 0.016 0.024cd
cl
-0.5
0.0
0.5
1.0
1.5
0.000 0.008 0.016 0.024
cl
RFOIL
NACA LTPT
Re = 3x106
RFOIL x 1.09
Cd
RFOIL x 1.09
29DUWIND, Delft University Wind Energy Institute
DU 96-W-180
Re = 3.0x106
-1.0
-0.5
0.0
0.5
1.0
1.5
0.00 0.01 0.02 0.03cd
cL
-1.0
-0.5
0.0
0.5
1.0
1.5
-10 0 10 20a (o)
cL
Delft
Stuttgart
RFOIL
RFOIL*1.09
30DUWIND, Delft University Wind Energy Institute
Roughness
31DUWIND, Delft University Wind Energy Institute
NACA 632-615
Re = 6.0x106
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
0.000 0.008 0.016 0.024cd
cl
-0.8
-0.4
0.0
0.4
0.8
1.2
1.6
-10 0 10 20a (o)
cl
Roughness off
Roughness on
32DUWIND, Delft University Wind Energy Institute
NACA 63-x15
Re=6x106
-5
-4
-3
-2
-1
0
1
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient, Cl,i
Zer
o-lif
t an
gle
(deg
rees
)
Roughness
Clean
RFOIL
33DUWIND, Delft University Wind Energy Institute
Roughness?
34DUWIND, Delft University Wind Energy Institute
NACA 643-x18
Re = 6.0x106
-1.0
-0.5
0.0
0.5
1.0
1.5
0.00 0.01 0.02 0.03cd
cL
-1.0
-0.5
0.0
0.5
1.0
1.5
-20 -10 0 10 20 30a (o)
cL
64-01864-21864-41864-618
35DUWIND, Delft University Wind Energy Institute
0.6
0.8
1
1.2
1.4
1.6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7
Design lift coefficient
Cl-
max
Clean
Wrap-around roughness
Naca 64-x18
Re=6x106
Reduction 18% - 20%
36DUWIND, Delft University Wind Energy Institute
Roughness configurations
• NACA wrap-around roughness (no. 60 grid distributed sparsely from 8% at the lower surface to 8% on the upper surface (worst case?)
• NASA roughness (no. 80 grid strips , 2.5 cm wide at both the upper and lower surface 8% chord stations
• Zigzag tape, various thicknesses and positions• Fixed transition on the leading edge in
calculations
37DUWIND, Delft University Wind Energy Institute
LS(1)-0417
Re = 6.0x106
-1.0
-0.5
0.0
0.5
1.0
1.5
2.0
0.000 0.015 0.030 0.045
cd
cl
-1.0
-0.5
0.0
0.5
1.0
1.5
2.0
-10 0 10 20 30
a (o)
cl
NACA roughness
NASA roughness
Free transition
38DUWIND, Delft University Wind Energy Institute
NACA 64-418
Re = 6.0x106
Grid roughness
-1.0
-0.5
0.0
0.5
1.0
1.5
0.00 0.01 0.02 0.03cd
cL
-1.0
-0.5
0.0
0.5
1.0
1.5
-20 -10 0 10 20 30a (o)
cL
NACA LTPT
RFOIL
RFOIL: b.l. tripped at x/c=5% u.s. and 5% l.s.
39DUWIND, Delft University Wind Energy Institute
0.4
0.6
0.8
1
1.2
1.4
1.6
0 2 4 6 8 10 12Rx10-6
Cl,max
Clean
zigzag tape 0.4 mm
Carborundum 60
Du 97-W-300Mod
40DUWIND, Delft University Wind Energy Institute
Conclusions
• The measured zero-lift angle of several NACA airfoils needs to be adjusted with absolute values ranging from 0.4 to 1 degree
• The maximum lift coefficients predicted with RFOIL match the LTPT data well at Re=3x106, but under predict the Cl,max at 6x106 by 3.5% up to 6.5% at Re=9x106
• Though it may be possible that the higher Cl,max in the LTPT data partly originates from the wall pressure method, RFOIL also under predicts the maximum lift measured with surface pressures.
41DUWIND, Delft University Wind Energy Institute
Conclusions (cntd)
• RFOIL consistently under predicts the drag coefficient with about 9% for a wide range of airfoils and Reynolds numbers
• NACA standard roughness causes a reduction in the lift coefficient of 18% to 20% for 18% thick airfoils from the NACA 64-series
• The effect on airfoil performance of various types of roughness has been measured in the past, but it is unclear what type of roughness may be expected, though wrap-round roughness may serve as a worst-case scenario
42DUWIND, Delft University Wind Energy Institute
How to proceed?
• Roughness investigations in the wind tunnel at the appropriate Reynolds numbers and field tests with zigzag tape on the blades are necessary to be able to better quantify the effect of blade soiling on the rotor performance
• Side-by side tests are necessary to better understand the amount of soiling during operation.