Transonic Buffet Control on 3D Turbulent Wings using Fluidic ......1 Transonic Buffet Control on 3D...
Transcript of Transonic Buffet Control on 3D Turbulent Wings using Fluidic ......1 Transonic Buffet Control on 3D...
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Transonic Buffet Control on 3D Turbulent Wings using Fluidic Devices
Part 1: Open loop study
J. Dandois 1, J.-B. Dor 2, P. Molton 3, A. Lepage 4 F. Ternoy 5, V. Brunet 1 and E. Coustols 2
1 Applied Aerodynamics Department 2 Aerodynamics and Energetics Modeling Departement 3 Fundamental and Experimental Aerodynamics Department 4 Aeroelasticity and Structural Dynamics Department 5 Model Design and Manufacturing Department
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Buffet phenomenon
- Buffet limits operational flight conditions of a given aircraft (Mach number, lift), which leads to a margin (30%) between CLcruise and CLbuffet_onset - Buffet control would provide more flexibility in wing design
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Plan
1) S3Ch wind tunnel tests (PRF BUFET’N Co & JTI SFWA WP112) => “research-type” tests to compare the efficiency of passive and
active VGs => acquisition of an extensive database for the validation of numerical
simulations (unsteady pressure transducers, PIV and LDV) => preparation of the S2MA WTT
1) S2MA wind tunnel tests (EC FP6 AVERT & PRF BUFET’N Co ) => final demonstration of the buffet control in an industrial-type wind
tunnel (open loop & closed-loop)
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Testing of active devices at the ONERA S3Ch WT Mechanical VGs Fluidic VGs: small nozzle M=2, Φ=1mm (continuous/pulsed)
S3Ch wind tunnel tests
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Flow control by mechanical VGs: α = 3.5°, Mp = 0.815
80% 70% 60% 50% Baseline
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Flow control by fluidic VGs: α = 3.5°, Mp = 0.815
80% 70% 60% 50% - Flow separation suppressed between Y/b = 60 and 80% - Results similar to mechanical VGs
Baseline
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y/b=70%-1.5
-1
-0.5
0
0.5
1
0 10 20 30 40 50 60 70 80 90 100
x/c(%)
-Kp
Baseline
2g/s (Cmu=2.3e-4)
1.8g/s (Cmu=2.1e-4)
1.6g/s (Cmu=1.8e-4)
1.35g/s (Cmu=1.5e-4)
1.2g/s (Cmu=1.4e-4)
1.1g/s (Cmu=1.3e-4)
1g/s (Cmu=4.3e-5)
0.8g/s (Cmu=3.4e-5)
0.7g/s (Cmu=2.2e-5)
0.5g/s (Cmu=1.1e-5)
JTI-SFWA 1.1.2 : S3Ch Wind Tunnel Tests
• Fluidic VGs: mass-flow rate effect
⟨ = 3.5°
- Fluidic VGs are effective for very low values of the mass-flux (2g/s)
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y/b=70%-1.5
-1
-0.5
0
0.5
1
0 10 20 30 40 50 60 70 80 90 100
x/c(%)
-Kp
Baseline
all active 2.4g/s(Cmu=2.8e-4)
1VG/2 active 2.2g/s(Cmu=2.5e-4)
1VG/3 active 2.1g/s(Cmu=2.4e-4)
1VG/4 active 0.9g/s(Cmu=1e-4)
1VG/5 active 0.7g/s(Cmu=8.1e-5)
1VG/6 active 1g/s(Cmu=1.1e-4)
1VG/7 active 0.8g/s(Cmu=9.2e-5)
• Fluidic VGs: spacing effect
⟨ = 3.5°
JTI-SFWA 1.1.2 : S3Ch Wind Tunnel Tests
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• Fluidic VGs: spanwise location effect
⟨ = 3.5° y/b=70%
-1.5
-1
-0.5
0
0.5
1
0 10 20 30 40 50 60 70 80 90 100
x/c(%)
-Kp
Baseline
VG 1 to 7 1.3g/s(Cmu=1.5e-4)
VG 8 to 13 0.9g/s(Cmu=1e-4)
VG 14 to 19 1g/s(Cmu=1.1e-4)
VG 20 to 25 1.1g/s(Cmu=1.3e-4)
JTI-SFWA 1.1.2 : S3Ch Wind Tunnel Tests
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Unsteady measurements: comparison of mechanical and fluidic VGs effects
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• Decrease of the RMS level on the pressure and on the accelerometers • Nearly same effect between passive and active VGs
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Mechanical VGs => BAY model in elsA
elsA RANS computation of the S3Ch model with passive VGs
M = 0.82, α = 3,5o (buffet for α>3,0o)
ReAMC = 2,8 106
Exp.
Good agreement between CFD results and experimental data if the mesh is fine enough to discretize each vortex
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Exp.
Fluidic VGs => Overset grid method
Good agreement between CFD results and experimental data
elsA RANS computation of the S3Ch model with fluidic VGs
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Peniche / Fuselage / Wing Wing cross-section:
OAT15A airfoil Wing span: 1.225m Chord length:
0.450m 0.225m ϕ=30°
ONERA S2MA WT
S2MA WTT
Devices tested: Baseline Configuration Mechanical VGs Fluidic VGs (continuous flow rate) Fluidic TED (continuous flow rate) designed with PPRIME
ONERA Half-model
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Baseline (α=4.25°) Mechanical VGs (α=3.5°)
Fluidic VGs (α=4.25° - Cµ=0.06%)
S2MA WTT: comparison between passive and fluidic VGs
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- Effect of Fluidic VG at Cµ=4.6 10-5 (3g/s) comparable to Mech. VG - Saturation efficiency on CL for Fluidic VGs at Cµ higher than 9.2 10-5
- BUT still efficient on decreasing unsteadiness (Kulites transducers)
Fluidic VGs configuration
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Fluidic VGs configuration
Lift gain maximum for a spanwise spacing of 46d
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Pulsed Fluidic VGs configuration
- Low pass filter behaviour of the shock oscillation - Frequency bandwidth of the shock around 160Hz
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Fluidic TED at Cμ=0.0027
M=0,82 Pi=0,6b
0
0,2
0,4
0,6
0,8
1
-2 -1 0 1 2 3 4 5 6 7
Alpha (°)
Cz
Baseline (192)FTED Cmu=0,0090 (472)FTED Cmu=0,0058 (474)FTED Cmu=0,0036 (475)FTED Cmu=0,0027 (477)Baseline (193)
Fluidic TED vs. Baseline Configuration
Mech. TED deflected at 30°
Fluidic TED configuration
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Comparisons at iso-CL
Fluidic TED configuration
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- Mechanical/Fluidic VGs delay buffet onset by 0.3° and 1° respectively - Fluidic TED delay buffet onset only in CL
Results summary
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- Mechanical/Fluidic VGs delay buffet onset both in the (M,α) and (M,CL) planes - Fluidic TED delay buffet onset only in the (M,CL) plane For more details see: “Buffet Characterization and Control for Turbulent Wings”,
Aerospace Lab, Vol. 6, 2013. http://www.aerospacelab-journal.org Next presentation: closed-loop buffet control by A. Lepage
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Results summary