Post on 19-Jul-2018
Bucharest, October 19th 2017
Coordinator :
Martin Wahlich (Airbus)
FULL-SCALE WIND-TUNNEL TEST OF ACTIVE FLOW CONTROL AT THE WING/PYLON/ENGINE JUNCTION
Soudakov V. (TsAGI), Amiryants G. (TsAGI)
Schloesser P. (Airbus), Bauer M. (Navasto),
Weigel P. (Fraunhofer), Bardet M. (NLR)
Ciobaca V., Gebhardt A., Wild J. (DLR)
Objectives
2 October 2017
To develop WT model,
install AFC hardware and
systems to suppress
separation
To prepare and carry-out
large scale WT tests
with/without AFC for TRL4
demonstration
Relatively small cutout
Large nacelle for
UHBR engine Standard nacelle
Relatively large cutout
Subsonic wind tunnel T-101 TsAGI
3
Test section dimensions:
Nozzle cross section 2414 m (elliptic)
Large-scale WT
Flow velocity up to 45-50 m/s
Re (MAC=3.259m) 11.2106
Total pressure atmospheric
Temperature environmental
M 0.15
October 2017
AFLONEXT model in WT
October 24, 2016 4
Total parts for
manufacturing: 1983
Total standard parts:
9807
Total parts: 11790
October 2017 4
DLR F-15 configuration
2.5D high-lift
Underwing throughflow nacelle for
UHBR engine
Sref =16.29 m2
MAC=3.259 m
Wing sweep angle 28°
5
CFD, CLmax regime
October 2017
•Separation in pylon wake
•Similar to aircraft
configuration
•Different critical AoA
Model
Aircraft
AFLoNext model overview
FLAP
SUPPORT OF THE
MODEL
SIDE PLATE INBOARD
TRAILING EDGE
WINGBOX
SLAT OUTBOARD
LEADING EDGE
LEADING EDGE
INBOARD
FAIRING INBOARD
NACELLE
PYLON
SIDE PLATE
OUTBOARD
SJA-insert
PJA - insert
BALANCE
SLAT
INBOARD
LEADING
EDGE
OUTBOARD
FAIRING
OUTBOARD
FAIRING OF THE
CCD - CAMERA
LENGTH OF MODEL ~ 7900 mm
WIDTH OF MODEL ~ 6000 mm
SPAN OF WING 5000 mm
SWEEP ANGLE 28°
WEIGHT ~5500 kg
6 October 2017
Leading edge for the SJA - insert
Top panel for SJA/PJA LE
Cover
Top panel for
SJA/PJA LE
SJA - insert
10 October 2017
Experimental results, strake
13
• NO stall due to separation in pylon
wake even without strake
• There is a potential for AFC
October 2017
with Strake
no Strake
Mini-tufts, with strake
14
AoA -> linear regime AoA -> ~CLmax
No separation
Separation
October 2017
V V
• Minitufts show that separation in pylon
wake starts to grow which can be
suppressed by AFC
• There is the deviation from linear CL(AoA)
curve which can be suppressed by AFC
Experiments, PJA, V=30 m/s
16
CL(AoA)
• Reference configuration with
strake
• Blue – PJA with Mj~0.6, close to
reference
• Brown – PJA with Mj~0.86
• Green – PJA with Mj~1
• Monotonic effect with increase of
jet intensity
October 2017
0.1
2 deg
Experiments, PJA, V=30 m/s, Cp, AoA=max
17
Cp
X
1.0
0.0
-1.0
-2.0
-3.0
-4.0
-5.0
-320-420-520-620-720
Прот. Отс. Сеч.1012;1 9 SLAT_11023;1 8 SLAT_11030;1 8 SLAT_11031;1 8 SLAT_11032;1 8 SLAT_1
V актуатор Конфиг G параметр актуатора30 баз LEX --- ---30 PJA LEX --- ---30 PJA LEX 1.25 Mj=130 PJA LEX 0.67 Mj=0.630 PJA LEX 0.98 Mj=0.86
Cp
X
1.0
0.0
-1.0
-2.0
-3.0
0 500 1000 1500
Прот. Отс. Сеч.1012;1 9 WING_11023;1 8 WING_11030;1 8 WING_11031;1 8 WING_11032;1 8 WING_1
V актуатор Конфиг G параметр актуатора30 баз LEX --- ---30 PJA LEX --- ---30 PJA LEX 1.25 Mj=130 PJA LEX 0.67 Mj=0.630 PJA LEX 0.98 Mj=0.86
Cp
X
1.0
0.0
-1.0
-2.0
1800 2050 2300 2550
Прот. Отс. Сеч.1012;1 9 FLAP_11023;1 8 FLAP_11030;1 8 FLAP_11031;1 8 FLAP_11032;1 8 FLAP_1
V актуатор Конфиг G параметр актуатора30 баз LEX --- ---30 PJA LEX --- ---30 PJA LEX 1.25 Mj=130 PJA LEX 0.67 Mj=0.630 PJA LEX 0.98 Mj=0.86
October 2017
Cp
X
1.0
0.0
-1.0
-2.0
2650 2900 3150
Прот. Отс. Сеч.1012;1 9 FLAP_21023;1 8 FLAP_21030;1 8 FLAP_21031;1 8 FLAP_21032;1 8 FLAP_2
V актуатор Конфиг G параметр актуатора30 баз LEX --- ---30 PJA LEX --- ---30 PJA LEX 1.25 Mj=130 PJA LEX 0.67 Mj=0.630 PJA LEX 0.98 Mj=0.86
Cp
X
1.0
0.0
-1.0
-2.0
3450 3700 3950
Прот. Отс. Сеч.1012;1 9 FLAP_31023;1 8 FLAP_31030;1 8 FLAP_31031;1 8 FLAP_31032;1 8 FLAP_3
V актуатор Конфиг G параметр актуатора30 баз LEX --- ---30 PJA LEX --- ---30 PJA LEX 1.25 Mj=130 PJA LEX 0.67 Mj=0.630 PJA LEX 0.98 Mj=0.86
Experiments, PJA, minitufts
18
AoA = max, No jet
Separation
upstream of
PJA
AoA = max, With jet
Separation Fully attached
downstream
of PJA
October 2017
V V
Experiments, PJA, different free-stream velocities
19
• Noticeable effect
for all speeds
October 2017
CL(AoA)
0.1
2 deg
CL(AoA)
0.1
2 deg
V=40 m/s V=48 m/s
With PJA
Reference, no jet
Experiments, PJA, no strake
20
• Monotonic increase of
effect due increase of
intensity
• DCL is approximately the
same as in case with strake
October 2017
V=48 m/s
CL(AoA)
0.1
2 deg
SJA, experiments, V=30 m/s
22
• Frequency sweep then AoA sweep with
optimal F
• No optimal F on balances
• Very small scale
• SJA effect within scale of accuracy /
repeatability
October 2017
CL
0.01
Frequency sweep, F
CL (AoA)
1 deg
0.1
Summary
23 October 2017
• WT model has been developed, PJA and SJA hardware and
systems have been installed
• Large-scale WT tests without/with PJA and SJA have been carried
out in T-101 TsAGI WT
• PJA essentially increases CL values near CLmax regime
• Cp-distributions and minitufts show that this increase is due to
suppression of separation in pylon wake region
• There is no essential difference in CL and minitufts due to SJA