Reynolds number influence on delta wing vortex · PDF fileTechnische Universität...
Transcript of Reynolds number influence on delta wing vortex · PDF fileTechnische Universität...
![Page 1: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/1.jpg)
Technische Universität München
1PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Reynolds number influence on Reynolds number influence on delta wing vortex flowsdelta wing vortex flows
TUMTUM--AER projectAER project
Outline
Background and expertise
Objectives and exploitation
ETW experiments – model & instrumentation
Partners – consortium
![Page 2: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/2.jpg)
Technische Universität München
2PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Background and expertise
Objectives and exploitation
ETW experiments – model & instrumentation
Partners – consortium
Outline
![Page 3: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/3.jpg)
Technische Universität München
3PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– basicsbasics
Angle of attack α
Boundary layer(laminar / turbulent)
Wing sweep φ(planform)
Leading-edge radius rN(airfoil)
Main parameters
Incident and surface flow
Geometry
rN
φ
U∞w
α
Evolution of large scale vortices … determine lift characteristics, maneuver capabilities and stability
Background
![Page 4: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/4.jpg)
Technische Universität München
4PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– basicsbasics
Vortex development depend on leading-edge sweep φ and angle of attack α40
2: Fully developedvortex, moving inboard
3: Span–wisefixed vortex
0
5
10
35
30
25
20
15
50 8555 60 65 70 75 80
α [°]
φ [°]
∆α
2 α
4 α
αmax
αBursting(trailing–edge)
Thin, planar wings;sharp leading–edgeThin, planar wings;sharp leading–edge
1: Vortex formation
4: Vortex bursting over the wing
1 α
3φW
laminar
turbulent
laminarturbulent
Background
![Page 5: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/5.jpg)
Technische Universität München
5PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– Re influence Re influence (secondary separation)
Separation line of secondary vortex
Laminarregion
Turbulentregion
Transition
xy
νxU
x∞=Re
y
–CP
y
–CP
uppercrit ,ReRe >Upper- / lower side:
Laminar / laminar : Rex < 0.9 x 106 = Recrit,upper
y
–CP
lowercrit ,ReRe >
Turbulent / laminar : 0.9 x 106 < Rex < 1.9 x 106
Turbulent / turbulent : Rex > 1.9 x 106 = Recrit,lower
Background
![Page 6: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/6.jpg)
Technische Universität München
6PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 2 (RTO(RTO--AVTAVT--113, RTO113, RTO--AVTAVT--183)183)
Expertise
![Page 7: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/7.jpg)
Technische Universität München
7PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 configuration 2 configuration –– Geometry Geometry
crb
= 0.
933
c rφ = 65°
Sharp LERounded LE
0.15 cr 0.10 cr
t = 0.034 cr
r/lµ = 0.15 %
Expertise
![Page 8: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/8.jpg)
Technische Universität München
8PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 2 configconfig. . –– TUMTUM––AERAER wind tunnel model wind tunnel model
Sharp leading-edgeRounded leading-edger/lµ = 0.0015
Expertise
![Page 9: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/9.jpg)
Technische Universität München
9PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 2 configconfig. . –– TUMTUM––AERAER wind tunnel model wind tunnel model
2/3 crlµmean aerodynamic chord
0.914 mb = 2swing span
65°φleading edge sweep1.865Λaspect ratio
0.448 m2Fwing area
0.980 mcrroot chord
Expertise
![Page 10: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/10.jpg)
Technische Universität München
10PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 2 configconfig. . –– TUMTUM––AERAER model instrumentation model instrumentation
crb
= 0.
933
c rφ = 65°
0.2 0.4 0.6 0.8 0.95
177 pressure pos.:diam. 0.3 mm
5 chord stations
0.15 cr 0.10 cr
t = 0.034 cr 133 steady sensors (PSI)
44 unsteady sensors (Kulites)
![Page 11: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/11.jpg)
Technische Universität München
11PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Laser light sheet Laser light sheet flow visualizationflow visualizationBurst leading–edge vortex; α = 30°:
x/cr = 0.20x/cr = 0.40x/cr = 0.60x/cr = 0.80x/cr = 0.95x/cr = 1.10
Expertise
![Page 12: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/12.jpg)
Technische Universität München
12PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Laser light sheet Laser light sheet flow visualizationflow visualizationFully developed leading–edge vortex; α = 18°:
Sharp leading edge Rounded leading edge
Expertise
![Page 13: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/13.jpg)
Technische Universität München
13PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow field Flow field –– mean velocitymean velocityPartly developed leading–edge vortex; α = 13°:
x/cr = 0.2, 0.4, 0.6, 0.8, and 0.95:
Expertise
![Page 14: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/14.jpg)
Technische Universität München
14PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow field Flow field –– turbulence intensityturbulence intensityPartly developed leading–edge vortex; α = 13°:
x/cr = 0.4x/cr = 0.4 x/cr = 0.6x/cr = 0.6 x/cr = 0.8x/cr = 0.8
urms/U∞urms/U∞
Expertise
![Page 15: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/15.jpg)
Technische Universität München
15PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow field Flow field –– turbulence intensityturbulence intensityBurst leading–edge vortex; α = 23°:
x/cr = 0.4x/cr = 0.4 x/cr = 0.6x/cr = 0.6 x/cr = 0.8x/cr = 0.8
urms/U∞urms/U∞
Expertise
![Page 16: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/16.jpg)
Technische Universität München
16PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Re = 2.0 x 106
α = 23°Re = 2.0 x 106
α = 23°
Surface pressure Surface pressure –– turbulence intensityturbulence intensity
![Page 17: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/17.jpg)
Technische Universität München
17PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Complex flow topology Complex flow topology –– Re influence / multiple vorticesRe influence / multiple vortices
Ma = 0.4 (const.)
Re = 1 x 106 Re = 2 x 106 Re = 3 x 106
URANS simulations
(Courtesy W. Fritz, AIAA Paper 2008-393)
Expertise
![Page 18: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/18.jpg)
Technische Universität München
18PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– Re influence Re influence
U∞
Laminarseparation
Turbulentseparation
Secondary vortex
Primary vortex
Inboard vortex
AttachmentSeparation
AttachmentSeparation
AttachmentSeparation
Topology ofvortex system
M = 0.14 Re = 2.0 x 106
α = 13°
Oil flow
Expertise
![Page 19: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/19.jpg)
Technische Universität München
19PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– Re influence Re influence
TUM – Oil flow
M = 0.14 Re = 2.0 x 106
α = 13°
DLR – TSP
VFE-2delta wing
KKK tests (T: 240 K – 150 K)(Courtesy R. Konrath)
Ma = 0.05 – 0.16
Re = 1 x 106 – 6 x 106
α = 5° – 28°
Expertise
![Page 20: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/20.jpg)
Technische Universität München
20PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Background and expertise
Objectives and exploitation
ETW experiments – model & instrumentation
Partners – consortium
Outline
![Page 21: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/21.jpg)
Technische Universität München
21PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– Re influenceRe influence
Separating shear layer
Vortex core (fully developed / bursting)
Boundary layer – secondary separation
φ
α = 30.0°
α = 25.0°
U∞
φ = 76°
0.02
0.28
0.20
0.10
∞′ Uu 2
Associated characteristic instabilities
Objectives and exploitation
![Page 22: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/22.jpg)
Technische Universität München
22PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– Re influenceRe influence
Re = 2.0 x 106
α = 18°Multiple vortex system Re = const.
α
Laminarseparation
Turbulentseparation
Objectives and exploitation
![Page 23: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/23.jpg)
Technische Universität München
23PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– Re influenceRe influence
α = 18°Re = 1·106
Rounded leading edge
Objectives and exploitation
![Page 24: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/24.jpg)
Technische Universität München
24PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Objectives Objectives
Analysis of aerodynamic characteristics and corresponding flow topologies – selected test cases
Improving flow physics knowledge and modeling
Vortex flow data base associated with significant Reynolds number variation
Extending the VFE-2 data base for high-fidelity CFD applications (hybrid RANS/LES methods)The test case is currently addressed within the research activities GARTEUR AG49 and ATAAC.
Objectives and exploitation
![Page 25: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/25.jpg)
Technische Universität München
25PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Flow physics Flow physics –– CFD challenges CFD challenges (Re impact)
GARTEUR AG49:Scrutinizing Hybrid RANS/LES methodsFor Aerodynamic Applications
(Implicit LES TUM-AER)
Test case 2.2: VFE-2 delta wing
ATAAC – Advanced Turbulence Simulation for Aerodynamic Application Challenges
Test case: ST08 Delta wing with sharp leading edge (VFE-2)
Test case: AC06 Full aircraft with small aspect ratio wing (FA5)
Objectives and exploitation
![Page 26: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/26.jpg)
Technische Universität München
26PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Background and expertise
Objectives and exploitation
ETW experiments – model & instrumentation
Partners – consortium
Outline
![Page 27: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/27.jpg)
Technische Universität München
27PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 Model 2 Model –– cryogenic testingcryogenic testing
Model designed for cryogenic testing
ETW experiments
![Page 28: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/28.jpg)
Technische Universität München
28PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
VFEVFE--2 Model 2 Model –– balance and stingbalance and sting
Balance: Wxxx suitable for ETW
ETW tail sting
ETW experiments
![Page 29: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/29.jpg)
Technische Universität München
29PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Test conditionsTest conditions
Flow parameterFlow parameter
• Ma ≈ 0.1 – 0.5 (load limit)
• Re ≈ 1 x 106 – 30 x 106
• α ≈ 0° – 35°
• V = const; Ma & Re variable
• q = const; T variable
• β = 0°
ETW experiments
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Technische Universität München
30PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Measured data and analysis Measured data and analysis
Aerodynamic characteristics …
Forces and moments
Development stages of dominant vortices …
Flowfield (PIV)
VFE-2KKK
(Courtesy R. Konrath)
ETW experiments
![Page 31: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/31.jpg)
Technische Universität München
31PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Background and expertise
Objectives and exploitation
ETW experiments – model & instrumentation
Partners – consortium
Outline
![Page 32: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/32.jpg)
Technische Universität München
32PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partner nationsPartner nations
Consortium
![Page 33: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/33.jpg)
Technische Universität München
33PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partner institutesPartner institutes
National Technical University of Athens, NTUA
WarsawUniversityof Technology
CzechAeronautical Research and Test Institute
Swedish DefenceResearch Agency
Consortium
![Page 34: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/34.jpg)
Technische Universität München
34PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Consortium Consortium –– linkslinks
GARTEUR AG49:CIRA, Cassidian, DLR, FOI, NLR, ONERA, TUM
National Technical University of Athens, NTUA
WarsawUniversityof Technology
CzechAeronautical Research and Test Institute
Consortium
![Page 35: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/35.jpg)
Technische Universität München
35PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partners Partners –– TUMTUM--AER AER (Institute of Aerodynamics and Fluid Mechanics)
Proposal initiative / preparation
Data analysis and exploitation – nucleus for future projects
Importance of proposed work (commitment of partners)
Knowledge improvement of vortex physics
Experimental database for high-fidelity CFD verification
Contribution to improved transition/turbulence modeling
Fostering activities in vortex flow analysis and testing
Participation
Definition and support of test program and data reduction
Contribution to vortex flow measuring techniques
![Page 36: Reynolds number influence on delta wing vortex · PDF fileTechnische Universität München 1 PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar Reynolds number influence on delta wing](https://reader037.fdocuments.in/reader037/viewer/2022110111/5a9e2dfe7f8b9a6a218bccc0/html5/thumbnails/36.jpg)
Technische Universität München
36PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partners Partners –– City University LondonCity University LondonBackground and expertise
Analysis of aerodynamic performance, flow control, aerodynamic optimization; in particular vortex flows and high-angle of attack aerodynamics Transition physics and turbulence modelingSubsonic wind tunnel facility; measurement techniques
Exploitation of data and results Re effects - enhancement of vortex flow analysis and modelingAnalysis of laminar-turbulence transition, shear-layer instabilities, vortex evolutionImproved understanding w.r.t vortex manipulation
Dr. S. Prince, Dr. D. Greenwell, Prof. C. AtkinsKey personnel (School of Engineering)
Consortium
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Technische Universität München
37PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partners Partners –– FOI, KTHFOI, KTH (Swedish Defence Research Agency
Royal Institute of Technology)Background and expertiseAdvanced modeling of flow physics (turbulence and transition)Development of CFD methods and in-house CFD solver (EDGE)CFD analysis of air-vehicle aerodynamic performance, flow control, aero-acoustic noise, as well as for other multi-disciplinary aerodynamic applicationsHybrid RANS-LES simulations of vortex flows in conceptual studies of delta wing and fighter models
Exploitation of data and results Validation for development of advanced URANS and hybrid RANS-LES methodsValidation of turbulence-resolving simulations in modeling local laminar-turbulence transition, shear-layer instabilities, vortex formation, bursting and sheddingIn-depth understanding towards vortex flow control in relation to flight stabilityExtrapolation to higher Re-number flow conditions
Key personnel Dr. S.-H. Peng (FOI), Prof. A. Rizzi (KTH), Prof. C. Hirschel
Consortium
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Technische Universität München
38PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partners Partners –– NTUANTUA (National Technical University of Athens)
Background and expertiseTesting of UAVs, airfoil sections, scaled wind turbine rotors, flow control concepts Flow predictions of vortical flows using various CFD models associated with fixed and rotary aircraft configurations Subsonic wind tunnel facility (M = 0.15); Force, PIV measurement techniques, …
Participation in EU projects
Exploitation of data and results
CFD based validation Support of PhD theses and post-doctoral research using data which will become available in this project
Key personnel (School of Mech. Eng., Fluids. Dept., Aero Lab.)Prof. K. Giannakoglou, Ass. Prof. S. Voutsinas, Ass. Prof. D. Mathoulakis
Consortium
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Technische Universität München
39PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partners Partners –– VZLUVZLU (Aeronautical Research and Test Institute, CZ)
Background and expertisedistinguished research and test center; center of excellencesubstantial computational capacities and skillsoperation of several wind tunnel facilities (Mach 0.2 ÷ 3.5)
Exploitation of data and results verification of URANS CFD code EDGEimprovement of CFD application for high-agility A/C, high-α-regimepossible extension of in-house flight dynamics analysis
Key personnel Dr. Z. Patek, Dr. J. Fiala, Dr. P. Vrchota
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Technische Universität München
40PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Partners Partners –– Warsaw University of TechnologyWarsaw University of TechnologyBackground and expertise
Faculty of Power and Aero. Eng. – center of excellence for CFD
Development of CFD methods CFD analysis of aircraft aerodynamic performance
Exploitation of data and results
Widening of experience to be used in preparation of 2 Ph.D. thesesImprovement of research methodology and education for aerospace students
Key personnel Prof. Z. Goraj
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Technische Universität München
41PD Dr.-Ing. C. Breitsamter, Dipl.-Ing. J.-U. Klar
Concluding remarksConcluding remarks
Research topic of high relevance for improving flow physics knowledge and high-fidelity numerical modeling
European research consortium established
W/T model and instrumentation available for cryogenic testing
Creating a sounded data base
Summary