ATLAS Aero Group - University of Patras
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ATLAS Aero Team - UPat ATLAS-V Design
2D Biplane CFD Results - Phase I
Spyridon Kontogiannis and Alexandros Kontogiannis
January 8, 2015
For the first phase of the CFD analysis the 2D Biplane arrangement with g=1, st=0.3 anddecalage=-3o with the S1210 airfoil was tested. The analysis was held with S-A and SST k-models using Fluent for the Reynolds number of 200k while the mesh was constructed usingGambit. The forces on the biplane airfoils were investigated for angles ranging from 0 to 14o
with a step of 2o.
In the next pages there is a brief report consisting mainly of plots and screenshots of thedata. The following are included:
Coefficient plots of pressure, lift, drag and moment.
Qualitative data of the static pressure, velocity field, turbulent kinetic energy, velocityprofile of BL and the pre-stall characteristics.
The purpose of this analysis was to validate that the arrangement is efficient and to providemore accurate results to account for viscous effects. The results were promising (high clmax,relatively low cd and cm for the operational angles and high stall angle) and the arrangementis considered fixed.
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ATLAS Aero Team - UPat ATLAS-V Design
Mesh with Gambit
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ATLAS Aero Team - UPat ATLAS-V Design
Cp Distributions
Spalart-Allmaras (1st order upwind discr. scheme)
- 2o Angle
- 4o Angle
- 6o Angle
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ATLAS Aero Team - UPat ATLAS-V Design
Spalart-Allmaras (2nd order upwind discr. scheme)
- 2o Angle
- 4o Angle
- 6o Angle
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ATLAS Aero Team - UPat ATLAS-V Design
SST k-omega (1st order upwind discr. scheme)
- 2o Angle
- 4o Angle
- 6o Angle
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ATLAS Aero Team - UPat ATLAS-V Design
SST k-omega (2nd order upwind discr. scheme)
- 2o Angle
- 4o Angle
- 6o Angle
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ATLAS Aero Team - UPat ATLAS-V Design
Lift Coefficient vs Angle
0 2 4 6 8 10 12 141
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
1.9
22D BIPLANE ANALYSIS g=1, st=0.3, dec=-3 S1210
Angle (deg)
LiftCoeffi
cient
SA 1st ord. upw.SA 2nd ord. upw.SSTkw 1st ord. upw.SSTkw 2nd ord. upw.
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ATLAS Aero Team - UPat ATLAS-V Design
Lift Coefficient vs Drag Coefficient
0 0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.161
1.1
1.2
1.3
1.4
1.5
1.6
1.7
1.8
1.9
22D BIPLANE ANALYSIS g=1, st=0.3, dec=-3 S1210
Drag Coefficient
LiftCoeffi
cient
SA 1st ord. upw.SA 2nd ord. upw.SSTkw 1st ord. upw.SSTkw 2nd ord. upw.
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ATLAS Aero Team - UPat ATLAS-V Design
Moment Coefficient vs Angle
0 2 4 6 8 10 12 140.06
0.08
0.1
0.12
0.14
0.16
0.18
0.22D BIPLANE ANALYSIS g=1, st=0.3, dec=-3 S1210
Angle (deg)
Mom
entCoeffi
cient[CG:(142mm,0,145mm)]
SA 1st ord. upw.SA 2nd ord. upw.SSTkw 1st ord. upw.SSTkw 2nd ord. upw.
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ATLAS Aero Team - UPat ATLAS-V Design
Qualitative Data
S-A - Contours of Static Pressure at 4o
S-A - Velocity Field at 4o
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ATLAS Aero Team - UPat ATLAS-V Design
SST k-omega - Turbulent Kinetic Energy (k) at 4o
0.4cTransition
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ATLAS Aero Team - UPat ATLAS-V Design
Boundary Layer
S-A - Fully Turbulent Velocity Profile at 8o
Turbulent BL/ Velocity Profile
SST k-omega - Laminar to Turbulent Velocity Profiles at 8o
Reverse Flow and TransitionLaminar Flow
Turbulent Flow
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ATLAS Aero Team - UPat ATLAS-V Design
Pre-Stall Characteristics
SST k-omega - Laminar Separation Bubble of upper airfoil at 14o
Laminar Separation Bubble
S-A - No Laminar Separation Bubble on upper airfoil at 14o
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ATLAS Aero Team - UPat ATLAS-V Design
SST k-omega - Laminar Separation Bubble of lower airfoil at 14o
SST k-omega - Transition and LSB of lower airfoil at 14o
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