Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows:
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| Format: | Abschlussarbeit Buch |
| Sprache: | English German |
| Veröffentlicht: |
Köln
DLR, Deutsches Zentrum für Luft- und Raumfahrt
2016
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| Ausgabe: | Als Manuskript gedruckt |
| Schriftenreihe: | Forschungsbericht DLR, Deutsches Zentrum für Luft- und Raumfahrt
2016,62 |
| Schlagworte: | |
| Online-Zugang: | Inhaltsverzeichnis |
| Beschreibung: | Mit 7 Tabellen und 319 Literaturstellen |
| Beschreibung: | V, 286 Seiten Illustrationen, Diagramme |
Internformat
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| 245 | 1 | 0 | |a Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows |c Marco Costantini, Deutsches Zentrum für Luft- und Raumfahrt, Institut für Aerodynamik und Strömungstechnik, Göttingen |
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Datensatz im Suchindex
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| adam_text | Table of contents
1 Introduction 1
1 1 Scope of work 5
1 2 Outline 10
2 Theoretical considerations and available knowledge from previous
work 11
2 1 An introduction to boundary-layer transition 11
2 2 The road to turbulence in two-dimensional boundary layers 13
221 Linear amplification of the disturbances (linear stability theory) 14
222 Boundary-layer receptivity to external disturbances 17
223 Non-linear amplification of the disturbances and breakdown to
turbulence 19
224 Transition region and measurement of boundary-layer transition 19
2 3 Boundary-layer stability modifiers 21
231 Streamwise pressure gradient 23
232 Surface mass transfer 24
233 Surface heat transfer 24
234 Combination of streamwise pressure gradient and surface heat
transfer 25
2 4 Transition prediction based on linear, local stability theory (eh
method) 26
2 5 Past work on the effect of surface imperfections on boundary-layer
stability and transition with emphasis on forward-facing steps 29
3 Experimental setup 37
3 1 Cryogenic Ludwieg-Tube Göttingen (DNW-KRG) 37
3 2 Design of the model cross-section 40
321 Numerical tools 41
322 Wind-tunnel model requirements and model cross-section shape 42
3 3 Wind-tunnel model 46
3 4 Instrumentation of the wind-tunnel model 50
341 Temperature-sensitive paint (TSP) measurement technique 51
342 Pressure taps and thermocouples 52
4 Data analysis 55
4 1 TSP data acquisition 55
4 2 Detection of boundary-layer transition 56
4 3 Definition and evaluation of the test parameters 59
5 Results 63
5 1 Smooth configuration 64
511 Effect of the Mach number 65
512 Effect of pressure gradient and wall temperature ratio and
comparison with published work 70
513 Summary of investigations with the smooth configuration 80
5 2 Step configurations 81
521 Effect of the step height 82
522 Effect of the chord Reynolds number 85
523 Effect of the streamwise pressure gradient 88
524 Effect of the wall temperature ratio 90
525 Effect of the Mach number 94
6 Discussion of the results 98
6 1 Combined effect of forward-facing steps and chord Reynolds number
98
6 2 Combined effect of forward-facing steps and streamwise pressure
gradient 101
621 Sensitivity of boundary-layer transition to the effect of forward-
facing steps at different pressure gradients 101
622 Summary and discussion of the results obtained at M=0 77 and
standard wall temperature ratio 106
6 3 Combined effect of forward-facing steps, pressure gradient, and
Mach number 112
II
6 4 Summary and discussion of the results at standard TJTaw and
comparison with data from previous work 116
641 Comparison with results from previous work 120
642 Increase in amplification factors (AN) due to forward-facing steps 127
6 5 Combined effect of forward-facing steps and wall temperature ratio 129
651 Step-1 configuration (h/0 _h 0 5) 130
652 Step-2 and step-3 configurations (0 5 h/ö ^ 1 5) 133
653 Analysis and discussion of the results 135
654 Effect of forward-facing steps on boundary-layer transition at the
same, reduced wall temperature ratio 145
655 Summary of the results obtained at different wall temperature
ratios in the presence of forward-facing steps 147
p
-
Conclusion 149
7 1 Summary 149
7 2 Outlook 153
Appendix 159
A
A l
Supplements to the introduction 159
Historical review of the effects of surface imperfections in past
laminar flow research 159
Flight envelope for hypothetical transport aircraft employing natural
laminar flow wings 161
Experimental setup 163
Results of boundary-layer computations and linear stability analysis
of the model cross-section 163
Challenges for the application at DNW-KRG of typical solutions for
low-speed transition experiments on flat plates 165
Model surface quality 167
Analysis of the surface quality at the step location 167
Analysis (and improvement) of model surface quality 170
III
B 4 Challenges for the application of other measurement techniques for
transition experiments at DNW-KRG 175
B 5 Temperature-sensitive paint used in the present work 177
B 6 Locations of pressure taps and thermocouples installed on the
PaLASTra model 181
C Data analysis 182
C 1 Post-processing of TSP data 182
C11 Image registration 185
C12 Mapping 185
C13 Transition detection algorithm 187
C14 Quantitative evaluation of surface temperature 189
C 2 General features of TSP results 191
C21 Turbulent wedges observed on the model surface 191
C22 Natural-transition front 194
C23 Transition location in the region close to the model trailing edge 196
C 3 Influence of the turbulent boundary layer developing on the wind-
tunnel side walls 199
C 4 Streamwise variation of the wall temperature ratio 204
D Results with the smooth configuration 206
D l Repeatability and reproducibility of the experimental results 206
D 2 Variation of the streamwise pressure gradient 208
D 3 Achievable variation of parameters 211
D 4 Effect of the chord Reynolds number 213
D 5 Effect of the Mach number (details) 216
D 6 Transition A-factors for the PaLASTra model at DNW-KRG 221
D 7 Comparison of transition Reynolds numbers at reduced wall
temperature ratio 224
D 8 Relative variation of transition Reynolds number as a function of
the wall temperature ratio for M=0 65 and 0 5 225
E Results with the step configurations 227
E l Repeatability and reproducibility of the experimental results 227
IV
E 2 Combined effect of forward-facing steps and streamwise pressure
gradient at M=0 77 228
E21 TSP results showing the change in sensitivity of boundary-layer
transition to forward-facing steps at different pressure gradients 230
E 3 Combined effect of forward-facing steps, pressure gradient, and
Mach number 231
E31 Sensitivity of boundary-layer transition to the effect of forward-
facing steps at different Mach numbers 240
E 4 Alternative correlation of the experimental data with results from
linear stability computations 242
E 5 Combined effect of forward-facing steps and wall temperature ratio
at M=0 65 and 0 5 244
E 6 Example for the change in sensitivity of boundary-layer transition to
variations in TJTcm 249
E 7 Conditions under which boundary-layer transition was sensitive to
changes in the wall temperature ratio at M=0 35 and 0 77 251
E 8 Combined effect of forward-facing steps and wall temperature ratio
with the roughness Reynolds number as non-dimensional step
parameter 253
E 9 Effect of forward-facing steps on boundary-layer transition at the
same, reduced wall temperature ratio for M=0 35, 0 5, and 0 65 255
References 261
Nomenclature 281
|
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| spelling | Costantini, Marco Verfasser aut Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows Marco Costantini, Deutsches Zentrum für Luft- und Raumfahrt, Institut für Aerodynamik und Strömungstechnik, Göttingen Als Manuskript gedruckt Köln DLR, Deutsches Zentrum für Luft- und Raumfahrt 2016 V, 286 Seiten Illustrationen, Diagramme txt rdacontent n rdamedia nc rdacarrier Forschungsbericht / DLR, Deutsches Zentrum für Luft- und Raumfahrt 2016-62 Mit 7 Tabellen und 319 Literaturstellen Dissertation Rheinisch-Westfälische Technische Hochschule Aachen 2016 Zusammenfassung in englischer und deutscher Sprache Oberflächentemperatur (DE-588)4221269-8 gnd rswk-swf Aerodynamik (DE-588)4000589-6 gnd rswk-swf Strömungstechnik (DE-588)4183719-8 gnd rswk-swf Reynolds-Zahl (DE-588)4177959-9 gnd rswk-swf Druckgradient (DE-588)4654440-9 gnd rswk-swf Oberflächenstruktur (DE-588)4130418-4 gnd rswk-swf Machzahl (DE-588)1132664268 gnd rswk-swf Grenzschichtumschlag (DE-588)4763105-3 gnd rswk-swf (DE-588)4113937-9 Hochschulschrift gnd-content Oberflächenstruktur (DE-588)4130418-4 s Oberflächentemperatur (DE-588)4221269-8 s Druckgradient (DE-588)4654440-9 s Grenzschichtumschlag (DE-588)4763105-3 s DE-604 Aerodynamik (DE-588)4000589-6 s Strömungstechnik (DE-588)4183719-8 s Machzahl (DE-588)1132664268 s Reynolds-Zahl (DE-588)4177959-9 s Forschungsbericht DLR, Deutsches Zentrum für Luft- und Raumfahrt 2016,62 (DE-604)BV011758990 2016,62 HEBIS Datenaustausch application/pdf http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&local_base=BVB01&doc_number=029452625&sequence=000001&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA Inhaltsverzeichnis |
| spellingShingle | Costantini, Marco Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows Forschungsbericht DLR, Deutsches Zentrum für Luft- und Raumfahrt Oberflächentemperatur (DE-588)4221269-8 gnd Aerodynamik (DE-588)4000589-6 gnd Strömungstechnik (DE-588)4183719-8 gnd Reynolds-Zahl (DE-588)4177959-9 gnd Druckgradient (DE-588)4654440-9 gnd Oberflächenstruktur (DE-588)4130418-4 gnd Machzahl (DE-588)1132664268 gnd Grenzschichtumschlag (DE-588)4763105-3 gnd |
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| title | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows |
| title_auth | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows |
| title_exact_search | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows |
| title_full | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows Marco Costantini, Deutsches Zentrum für Luft- und Raumfahrt, Institut für Aerodynamik und Strömungstechnik, Göttingen |
| title_fullStr | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows Marco Costantini, Deutsches Zentrum für Luft- und Raumfahrt, Institut für Aerodynamik und Strömungstechnik, Göttingen |
| title_full_unstemmed | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows Marco Costantini, Deutsches Zentrum für Luft- und Raumfahrt, Institut für Aerodynamik und Strömungstechnik, Göttingen |
| title_short | Experimental analysis of geometric, pressure gradient and surface temperature effects on Boundary-Layer transition in compressible high Reynolds number flows |
| title_sort | experimental analysis of geometric pressure gradient and surface temperature effects on boundary layer transition in compressible high reynolds number flows |
| topic | Oberflächentemperatur (DE-588)4221269-8 gnd Aerodynamik (DE-588)4000589-6 gnd Strömungstechnik (DE-588)4183719-8 gnd Reynolds-Zahl (DE-588)4177959-9 gnd Druckgradient (DE-588)4654440-9 gnd Oberflächenstruktur (DE-588)4130418-4 gnd Machzahl (DE-588)1132664268 gnd Grenzschichtumschlag (DE-588)4763105-3 gnd |
| topic_facet | Oberflächentemperatur Aerodynamik Strömungstechnik Reynolds-Zahl Druckgradient Oberflächenstruktur Machzahl Grenzschichtumschlag Hochschulschrift |
| url | http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&local_base=BVB01&doc_number=029452625&sequence=000001&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA |
| volume_link | (DE-604)BV011758990 |
| work_keys_str_mv | AT costantinimarco experimentalanalysisofgeometricpressuregradientandsurfacetemperatureeffectsonboundarylayertransitionincompressiblehighreynoldsnumberflows |