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Aerodynamic DepartmentInstitute of Aviation
WindWind TunnelTunnel TestsTestsff T b lT b l Ai f ilAi f il
WindWind TunnelTunnel TestsTestsff T b lT b l Ai f ilAi f ilof of TurbulentTurbulent AirfoilAirfoilss
for AC1for AC1 & AC2& AC2 AircraftAircraftof of TurbulentTurbulent AirfoilAirfoilss
for AC1for AC1 & AC2& AC2 AircraftAircraftfor AC1for AC1 & AC2& AC2 AircraftAircraftfor AC1for AC1 & AC2& AC2 AircraftAircraft
Jerzy Żółtak
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Head of CFD Group, Institute of Aviation
Aerodynamic DepartmentInstitute of Aviation
Wind Wind Tunnel
TestsTunnel
TestsTestsof ILL518
Testsof ILL518of ILL518
Turbulent Airfoil withof ILL518
Turbulent Airfoil withFlap for AC1 AircraftFlap for AC1 Aircraft
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation
WTT of ILL518 Turbulent Airfoil for AC1 (1)
The tested models h
The test of the ILL518 airfoil were carried out in the IoA T3 low-speed wind tunnel with open test section of 5 m diameter.
The tested models has achord 1 m and a span 1.73 m.The model is equipped inendplates of 1.8 m diameter.
The model of ILL518 airfoil section with flap in T3 Ø5m wind tunnel test section
pThe model was equippedwith pressure tap of diameterof 0.5 mm. The amount ofmeasurement points on a basic model was 59, and on a model with a flap – 52 on the main part of the airfoilon the main part of the airfoiland 29 on the flap.
The wake rake used for CD determination is consistent of 83 total pressure tubes and 4 static pressure tubes for measurements in wake The wake rake istubes and 4 static pressure tubes for measurements in wake. The wake rake is located at 0.75 of chord model trailing edge.For measurements of a pressure distribution on the airfoil and in a wake a four-module switch valve SCANIVALVE 48 DGM equipped with strain gauge
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
four module switch valve SCANIVALVE 48 DGM equipped with strain gauge pressure sensors DRUCK PDCR22 was used.
Aerodynamic DepartmentInstitute of Aviation
WTT of ILL518 Turbulent Airfoil for AC1 (2)
Test Programme: The first stage of research was the measurement of aerodynamic characteristics
of the basic airfoil – without a flap - ILL518. The research was carried out for six Reynolds numbers Re = 1, 1.4, 1.6, 2.65, 2.78, 3 106.
The second stage of research was The second stage of research wasthe measurement of aerodynamiccharacteristics of the ILL51 airfoilwith deflected flap, with and
Geometry of the ILL518 airfoil(without flap) tested in IoA wind tunnel
without the simulated contaminationof the leading edge of the airfoil.These tests were made for Reynolds
number Re = 2 65 106number Re = 2.65 106
for angles of the flapdeflection of k = 040°.
Proposed flap
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Proposed flap kinematics of a ILL518 airfoil
Aerodynamic DepartmentInstitute of Aviation Aerodynamic Characteristics: Effect of Reynolds Number
WTT of ILL518 Turbulent Airfoil for AC1 (3)
CDCL
Cruise Configuration
ΔC = 0 005ΔCD = 0.005
ΔCL=0.2CL
Cm ΔCm = 0.04
ΔCL = 0.2
m
Δα=4° ΔCL=0.2
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
CLα [°]L
Aerodynamic DepartmentInstitute of Aviation
WTT of ILL518 Turbulent Airfoil for AC1 (4) Aerodynamic Characteristics: Effect of Reynolds Number
ΔCL = 0.1Cruise
ConfigurationL g
CLmax
CDminCDmin
ΔCD = 0 001Kmax = (L/D)max
ΔCD 0.001
Kmax= 10
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation Aerodynamic Characteristics: Effect of Flap Deflection
WTT of ILL518 Turbulent Airfoil for AC1 (5)
For tested angles of flap deflection, in addition to the condition of CLmax, increase, the balance of drag in a range of
l d l f C d lcommonly used values of CL, and alsoincrease of pitching moment has been analyzed.
Re=2.65106
CL
L/D
ΔCL = 0.4
L/D
ΔL/D = 20High Lift Configuration
CLL
ΔCLmax
CLmax
δ [°]ΔCL = 0.4
ΔCL = 0.4
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
α [°] δf [°]δf [°]
Aerodynamic DepartmentInstitute of Aviation
WTT of ILL518 Turbulent Airfoil for AC1 (6) Aerodynamic Characteristics: Effect of Flap Deflection
Taking into account results of the analysis for takeoff configuration the angle of flap deflection δk = 15° and for landing configuration deflection δk = 35° were down selected.
tion
CL CDon
figur
a
ΔCL = 0.4
ΔCD = 0.01
ΔC = 1
ndin
g C
o
CL
C
ΔCL= 1
Re= 2.65 106
f and
Lan
Δα=6°
Cm ΔCL= 1
Take
off Δα 6
ΔCm= 0.1
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
CLα [°]
Aerodynamic DepartmentInstitute of Aviation
WTT of ILL518 Turbulent Airfoil for AC1 (7) Aerodynamic Characteristics: Effect of Roughness
Carborundum strip location and size
High Lift Configuration
CL The carborundum powder on strips was used to simulate the
ΔCL = 0.4
leading edge effect contamination by an icing or/and insects.
Carborundum strip on the surface of the airfoil model
ΔC = 0 1Cm
CD
ΔCm = 0.1mΔCD = 0.01
Δ 8°Δ 8°Δα=8°
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
α [°] α [°]α [°]
Δα=8°Δα=8° Δα=8°
Aerodynamic DepartmentInstitute of Aviation Comparison of experimental and the numerically
di t d di t ib ti f i f il ith t d ith fl
WTT of ILL518 Turbulent Airfoil for AC1 (8)
predicted pressure distributions for airfoil without and with flap
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation Comparison of experimental and the numerically
di t d ti h t i ti f i f il ith fl
WTT of ILL518 Turbulent Airfoil for AC1 (9)
predicted section characteristics for airfoil with flap
ΔCD = 0.01
ΔCL = 0.4ΔCL = 0.4 Δα=6°
Δα=6° ΔC 0 1
Δα=6°
Δα 6 ΔCm = 0.1
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation
Wind T l
Wind T lTunnel
TestsTunnel
TestsTests of ILM115 Turbulent
Tests of ILM115 Turbulent
Airfoil for AC2 AircraftAirfoil for AC2 Aircraft
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (1) .
The wind tunnel test was performed in the trisonicperformed in the trisonic wind tunnel N-3
The test was aimed to evaluate the section characteristics CL(α), CD(α) and
Cm(α) of the ILM-115 airfoil over wide the Mach number range M=0.3-0.82
The drag divergence and buffet onset boundaries were determined based on
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
the test results
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (2) .
The 2D ILM-115 airfoil model of 200 mm chord equipped with 69 pressure orifices(d=0.5mm) was used to measure the lift and pitching moment coefficients
A wake rake mounted at the model midspan and located one chord behind modeltrailing edge was used to measure the drag coefficient.The wake was equippedwith 111 total-pressure tubes and 3 static-pressure tubes
Buffet onset was detected by the first divergence from constant part of the modelroot bending moment measured by using strain gauges bridge against the angleof attack
Th t t d t d ith f d fi d t iti f b d l i
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
The test was conducted with free and fixed transition of boundary layer usingcarborund grains
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (3) Aerodynamic Characteristics
Re nolds N mber 2 989 Macha Number: 0.716
Run Number: 67.08PERFORATED WALLSILM115_AC2/T_CESAR
CL = design minα = -0.40o
Priority 1: cruise M = 0.716, Re = 2.95106
CL
cm = -0.0778 cd = 0.0062 cl = 0.214 alpha = -0.40 [deg.]
Nominal Angle of Attack: 0.000Reynolds Number: 2.989Run Number: 67.08
Cp*
-2.0
-1.5
-1.0
upper surface
lower surface
0.4
0.6
0.8
1.0
α 0.40
ΔCL = 0.1ΔCD = 0.002ΔCm = 0.1
Δα = 1
CLCDCm
sing
Dat
e: 1
8-04
-08/
8-Se
p-20
08
-0.5
0.0
0.5
Cp
-0 8
-0.6
-0.4
-0.2
0.0
0.2
m
Tset
/Pos
tpro
cess
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.01.0
x
-1.0
-0.8
Nominal Angle of Attack: 1 000Reynolds Number: 3.007 Macha Number: 0.715
Run Number: 67.08PERFORATED WALLSILM115_AC2/T_CESAR
-2.0
CL = design max
α = 0.42o
cm = -0.0737 cd = 0.0066 cl = 0.331 alpha = 0.42 [deg.]
Nominal Angle of Attack: 1.000
Cp*
-1.5
-1.0
-0.5Cp
upper surface
lower surface
0.4
0.6
0.8
1.0
oces
sing
Dat
e: 1
8-04
-08/
8-Se
p-20
08
0.5
0.0
0.5
1 0
C
-0.8
-0.6
-0.4
-0.2
0.0
0.2
Cm requirement
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Tset
/Pos
tpro
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.01.0
x
-1.0
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (4) Aerodynamic Characteristics
CL = design min
Priority 2: cruise M = 0.61, Re = 2.6106
Lα = 1.32o
ΔCL = 0.1ΔCD = 0.002ΔC 0 1
CLΔCm = 0.1 CDCm
Reynolds Number: 2.657 Macha Number: 0.610
Run Number: 65.08PERFORATED WALLSILM115_AC2/T_CESAR
-3 0
CL = design maxα = 3.01o
Δα = 2
cm = -0.0577 cd = 0.0096 cl = 0.633 alpha = 3.01 [deg.]
Nominal Angle of Attack: 4.000
Cp*
3.0
-2.5
-2.0
-1.5
p
upper surface
lower surface
0.4
0.6
0.8
1.0
essi
ng D
ate:
18-
04-0
8/8-
Sep-
2008
-1.0
-0.5
0.0
0.5
Cp
-0.8
-0.6
-0.4
-0.2
0.0
0.2
Cm requirement
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Tset
/Pos
tpro
ce
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.01.0
x
-1.0
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (5) Aerodynamic Characteristics
Macha Number: 0 693PERFORATED WALLSILM115_AC2/T_CESAR
CL = design min0 39o
Priority 3: cruise M = 0.694, Re = 2.9106
cm = -0.0757 cd = 0.0064 cl = 0.213 alpha = -0.39 [deg.]
Nominal Angle of Attack: 0.000Reynolds Number: 2.923
Macha Number: 0.693Run Number: 66.08
Cp*
-2.0
-1.5
-1.0
upper surface
lower surface
0.6
0.8
1.0
α = 0.39o
ΔCL = 0.1ΔCD = 0.002ΔC 0 1
Δα = 1
CLCDCm
g D
ate:
18-
04-0
8/8-
Sep-
2008
-0.5
0.0
0.5
Cp
-0.6
-0.4
-0.2
0.0
0.2
0.4ΔCm = 0.1
Reynolds Number: 2.940 Macha Number: 0.694
Run Number: 66.08PERFORATED WALLSILM115_AC2/T_CESAR
-2 0
Tset
/Pos
tpro
cess
ing
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.01.0
x
-1.0
-0.8
CL = design maxα = 0.44o
cm = -0.0726 cd = 0.0069 cl = 0.328 alpha = 0.44 [deg.]
Nominal Angle of Attack: 1.000
Cp*
2.0
-1.5
-1.0
p
upper surface
lower surface
0.4
0.6
0.8
1.0
essi
ng D
ate:
18-
04-0
8/8-
Sep-
2008
-0.5
0.0
0.5C
p
-0.8
-0.6
-0.4
-0.2
0.0
0.2
Cm requirement
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Tset
/Pos
tpro
ce
0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.01.0
x
-1.0
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (6) Shadowgraphs: flow visualization
CL design min) CLmax design expectedCL design max
1 6Pr
iorit
y M
= 0
.71
2Pr
iorit
y 2
M =
0.6
1P
3 4Pr
iorit
y 3
M =
0.6
94
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
P M
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (7) Aerodynamic characteristics: effect of Mach Number
CLmax
ΔCL=0.5
Lmax
Δα=0.1
α(CL=0)α(CL=0)
dCL/dα
CDmin
Cm(CL=0)
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (8) Aerodynamic characteristics: effect of Mach Number
Comparison of the experimental andC experimental and calculated (H code) drag divergence boundaries
ΔC = 0 1
CL
MDD(CL) with design liftcoefficient range andcomparison of the
ΔCL = 0.1
experimental buffetonset boundary MBO (CL) with required maximumwith required maximum lift coefficients CLmax
including a buffetingi f 0 5 f thΔM = 0 1 margin of 0.5g for the
ILM-115 airfoil atRe~4*106M
ΔM = 0.1
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
Aerodynamic DepartmentInstitute of Aviation
WTT of ILM115 Turbulent Airfoil for AC2 (9) Aerodynamic Characteristics: Low Mach Number (M=0.3)
CL _(CD) M=0.3 Re= 1.35e6CL CD M 0 3 061 f t llΔα=1
CL
CLmax for M = 0.3 (lower Mach number available in N-3 trisonic tunnel)
CL_CD_M=0.3_run061_ free trans_s walls
ΔCL=0.1Δα=1
CD ΔCD=0.01 ΔCL=0.2
0 5 0 3 0 1 0 1 0 3 0 5 0 7 0 9 1 1 1 3 1 5
Cm
CL
Cm _(CL) M=0.3 Re=1.35e6Cm_CL_M=0.3 run061_free trans_s walls
CmΔCL=0.2
ΔC =0 05
M = 0.3, Re = 1.35106,
free transition, solid walls
CL_Alpha_M=0.3_Re=01.35e6CL_alpha_M=0.3_run61_solid walls_free trans
ΔCm 0.05
α[°] CL
Influence of a lam/tur transition: M= 0.3÷0.8, perforated walls, the carborundum powder on strips
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009
the carborundum powder on stripsMain effect: the loss in CLmax due about 6% for M = 0.3, Re = 1.35106
Aerodynamic DepartmentInstitute of Aviation Comparison of experimental and the numerically
di t d ti h t i ti f i f il ith fl
WTT of ILM115 Turbulent Airfoil for AC2 (10)
predicted section characteristics for airfoil with flap
Validation of numerical results
airfoil: ILM 115
Ma = 0.61
Re = 2.66*106
Aerodynamic design of Small Aircraft, Training Workshop, Prague, 18-19 March 2009