Scramjet propulsion:
Gespeichert in:
| Format: | Buch |
|---|---|
| Sprache: | English |
| Veröffentlicht: |
Reston
American Institute of Aeronautics and Astronautics
2000
|
| Schriftenreihe: | Progress in astronautics and aeronautics
189 |
| Schlagworte: | |
| Online-Zugang: | Inhaltsverzeichnis |
| Beschreibung: | XXVII, 1293 S. Ill., graph. Darst. |
| ISBN: | 1563473224 |
Internformat
MARC
| LEADER | 00000nam a2200000 cb4500 | ||
|---|---|---|---|
| 001 | BV013813106 | ||
| 003 | DE-604 | ||
| 005 | 20010711 | ||
| 007 | t | ||
| 008 | 010710s2000 ad|| |||| 00||| eng d | ||
| 020 | |a 1563473224 |9 1-56347-322-4 | ||
| 035 | |a (OCoLC)46734717 | ||
| 035 | |a (DE-599)BVBBV013813106 | ||
| 040 | |a DE-604 |b ger |e rakwb | ||
| 041 | 0 | |a eng | |
| 049 | |a DE-91G |a DE-706 |a DE-634 |a DE-83 | ||
| 050 | 0 | |a TL507 | |
| 082 | 0 | |a 629.1 |2 21 | |
| 082 | 0 | |a 629.134/3535 |2 21 | |
| 084 | |a VER 636f |2 stub | ||
| 084 | |a VER 516f |2 stub | ||
| 084 | |a MAS 590f |2 stub | ||
| 245 | 1 | 0 | |a Scramjet propulsion |c ed. by E. T. Curran ... |
| 264 | 1 | |a Reston |b American Institute of Aeronautics and Astronautics |c 2000 | |
| 300 | |a XXVII, 1293 S. |b Ill., graph. Darst. | ||
| 336 | |b txt |2 rdacontent | ||
| 337 | |b n |2 rdamedia | ||
| 338 | |b nc |2 rdacarrier | ||
| 490 | 1 | |a Progress in astronautics and aeronautics |v 189 | |
| 650 | 4 | |a Avions - Statoréacteurs à combustion supersonique | |
| 650 | 4 | |a Propulsion par réaction | |
| 650 | 4 | |a Airplanes |x Scramjet engines | |
| 650 | 4 | |a Jet propulsion | |
| 650 | 0 | 7 | |a Raumfahrzeug |0 (DE-588)4048579-1 |2 gnd |9 rswk-swf |
| 650 | 0 | 7 | |a Raketentriebwerk |0 (DE-588)4176905-3 |2 gnd |9 rswk-swf |
| 650 | 0 | 7 | |a Überschallstaustrahltriebwerk |0 (DE-588)4427457-9 |2 gnd |9 rswk-swf |
| 650 | 0 | 7 | |a Überschallflugzeug |0 (DE-588)4186622-8 |2 gnd |9 rswk-swf |
| 650 | 0 | 7 | |a Hyperschallbereich |0 (DE-588)4161092-1 |2 gnd |9 rswk-swf |
| 650 | 0 | 7 | |a Luftstrahltriebwerk |0 (DE-588)4128278-4 |2 gnd |9 rswk-swf |
| 689 | 0 | 0 | |a Raumfahrzeug |0 (DE-588)4048579-1 |D s |
| 689 | 0 | 1 | |a Raketentriebwerk |0 (DE-588)4176905-3 |D s |
| 689 | 0 | 2 | |a Überschallflugzeug |0 (DE-588)4186622-8 |D s |
| 689 | 0 | 3 | |a Luftstrahltriebwerk |0 (DE-588)4128278-4 |D s |
| 689 | 0 | 4 | |a Überschallstaustrahltriebwerk |0 (DE-588)4427457-9 |D s |
| 689 | 0 | 5 | |a Hyperschallbereich |0 (DE-588)4161092-1 |D s |
| 689 | 0 | |8 1\p |5 DE-604 | |
| 700 | 1 | |a Curran, E. T. |e Sonstige |4 oth | |
| 830 | 0 | |a Progress in astronautics and aeronautics |v 189 |w (DE-604)BV001890233 |9 189 | |
| 856 | 4 | 2 | |m GBV Datenaustausch |q application/pdf |u http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&local_base=BVB01&doc_number=009444379&sequence=000001&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA |3 Inhaltsverzeichnis |
| 999 | |a oai:aleph.bib-bvb.de:BVB01-009444379 | ||
| 883 | 1 | |8 1\p |a cgwrk |d 20201028 |q DE-101 |u https://d-nb.info/provenance/plan#cgwrk | |
Datensatz im Suchindex
| _version_ | 1804128638447124480 |
|---|---|
| adam_text | SCRAMJET PROPULSION EDITED BY E.T. CURRAN DEPARTMENT OF THE AIR FORCE
DAYTON, OH S.N.B. MURTHY PURDUE UNIVERSITY WEST LAFAYETTE, IN VOLUME 189
PROGRESS IN ASTRONAUTICS AND AERONAUTICS PAUL ZARCHAN, EDITOR-IN-CHIEF
CHARLES STARK DRAPER LABORATORY, INC. CAMBRIDGE, MASSACHUSETTS PUBLISHED
BY THE AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS, INC. 1801
ALEXANDER BELL DRIVE, RESTON, VIRGINIA 20191-4344 CONTENTS PREFACE XXI
INTRODUCTION XXIII I. INTERNATIONAL EFFORTS XXIII II. INLETS,
COMBUSTORS, AND FUELS XXIV III. OVERALL SYSTEMS XXIV IV. FUTURE
DEVELOPMENTS XXV V. CLOSING COMMENTS XXV REFERENCES XXVI CHAPTER 1
SCRAMJET TESTING IN THE T3 AND T4 HYPERSONIC IMPULSE FACILITIES 1
NOMENCLATURE 1 I. HISTORY, AIMS, AND DEVELOPMENTS 2 II. FACILITY AND
INSTRUMENTATION 5 III. FUEL-INJECTION SYSTEMS 6 A. WALL-INJECTION
COMBUSTION RESULTS 8 B. WALL-INJECTION FILM-COOLING RESULTS 10 C.
PORT-INJECTION RESULTS 11 D. CENTRAL INJECTION 13 IV. COMBUSTION/MIXING
PROCESSES 17 A. MIXING CONTROLLED COMBUSTION 18 B. KINETICALLY
CONTROLLED COMBUSTION . . . ~. * 18 C. - SHOCK-INDUCED IGNITION 19 D.
SHOCK-INDUCED MIXING 20 V. SIMPLE THEORETICAL COMBUSTOR AND THRUST MODEL
21 VI. EXPERIMENTAL RESULTS OF SPECIFIC IMPULSE ** 25 VII. EFFECTS OF
ATOMIC OXYGEN AND NITRIC OXIDE IN THE FREESTREAM . . 30 VIII. DIFFERENT
FUELS 32 A. HYDROCARBON FUELS 32 B. SILANE-ENRICHED FUELS 34 IX.
INTEGRATED SCRAMJET MEASUREMENTS 35 X. SKIN-FRICTION MEASUREMENTS 40 XL
DISCUSSION AND REVIEW 42 ACKNOWLEDGMENTS 43 BIBLIOGRAPHY 43 CHAPTER 2
SCRAMJET DEVELOPMENTS IN FRANCE 47 I. HISTORICAL OVERVIEW 47 II. BASIC
RESEARCH ON DIFFUSION FLAME COMBUSTION (1962-1967) . . 49 VII VIII
CONTENTS A. COMBUSTION IN A CYLINDRICAL DUCT 49 B. FREEJETTEST 55 C.
COMBUSTION IN A DIVERGENT DUCT 56 D. SYNTHESIS 59 III. ESOPE PROGRAM
(1966-1973) .59 A. ORIGIN AND PRINCIPAL AIMS 59 B. STUDIES RESULTS 63 C.
SYNTHESIS 80 IV. STUDIES ON SHOCK-INDUCED COMBUSTION 81 A. PRINCIPLE 81
B. ENSMA AND LATECAM STUDIES 82 V. PREPHA PROGRAM (1992-1997) 84 A.
ORIGIN AND PRINCIPAL AIMS 84 B. SYSTEM STUDIES 85 C. DEVELOPMENT OF NEW
TEST FACILITIES 88 D. NUMERICAL MEANS 90 E. DEVELOPMENT OF SCRAMJET
COMPONENTS 93 F. MATERIALS AND COOLED STRUCTURES 101 G. FLIGHT TESTING
101 VI. PERSPECTIVES 103 A. SPACE APPLICATION 106 B. MISSILE APPLICATION
109 REFERENCES 112 CHAPTER 3 SCRAMJET INVESTIGATIONS WITHIN THE GERMAN
HYPERSONICS TECHNOLOGY PROGRAM (1993-1996) 119 I. GERMAN HYPERSONICS
TECHNOLOGY PROGRAM AND SCRAMJET-RELATED ACTIVITIES -.--... 119 A. GERMAN
HYPERSONICS TECHNOLOGY PROGRAM 119 B. SCRAMJET RELATED ACTIVITIES WITHIN
THE HTP 120 II. THEORETICAL INVESTIGATIONS FOR SCRAMJET INTAKE DESIGNS .
. . . . . 121 A. ACTIVITIES AT DASA-MT633 . . . . . . 121 B. ACTIVITIES
AT RWTH AACHEN 131 III. THEORETICAL AND EXPERIMENTAL INVESTIGATIONS OF
SCRAMJET COMBUSTION AT TSAGI AND DLR LAMPOLDSHAUSEN . 137 A. COMBUSTOR
MODEL DESIGN 137 B. FUEL-INJECTION MODULES 140 C. TEST RESULTS 140 IV.
FREEJET WIND-TUNNEL TESTING OF SCRAMJET PROPULSION SYSTEMS AT TSAGI 144
A. SCRAMJET PROPULSION SYSTEM MODEL CONCEPT 144 B. TESTING FOCUS 145 C.
TEST RESULTS 145 V. CONSIDERATIONS FOR FLIGHT TESTING SMALL-SCALE
SCRAMJET MODULES USING THE RADUGA-D2 FLYING TESTBED . . . . . . 149 A.
OBJECTIVES FOR FLIGHT TESTING 149 CONTENTS IX B. RADUGA-D2 FLYING
TESTBED 149 C. FLIGHT TEST TRAJECTORY AND INTEGRATION OF SCRAMJET IN THE
RADUGA-D2 150 REFERENCES 158 CHAPTER 4 SCRAMJET ENGINE RESEARCH AT THE
NATIONAL AEROSPACE LABORATORY IN JAPAN 159 NOMENCLATURE 159 I.
INTRODUCTION 160 II. ENGINE MODEL 161 A. INLET 164 B. STRUTS AND RAMPS
164 C. ISOLATOR, FUEL INJECTOR, AND COMBUSTOR 165 D. COMBUSTOR
DOWNSTREAM SECTION AND NOZZLE 169 E. LH 2 -COOLED MODEL 170 III. TEST
FACILITY 170 A. OUTLINE 170 B. COMPONENTS 172 C. CALIBRATION OF THE RJTF
174 IV. MEASUREMENTS 177 A. GENERAL FEATURES 177 B. ENGINE EXIT SURVEY
178 V. 5 TEST RESULTS 179 A. GENERAL FEATURES OF THE ENGINE OPERATION
179 B. MACH4TESTS 187 C. MACH 6 TESTS 191 D. MACH 8 TESTS 199 E.
LIQUID-HYDROGEN-COOLED ENGINE TESTS 202 VI. SUPPLEMENTARY STUDIES FOR
ENGINE TESTING . :-.- 203 A. 1 COMPUTATIONAL FLUID DYNAMICS 203 B.
CHEMICAL QUENCHING IN GAS-SAMPLING PROBES 206 C. SUBSCALE WIND-TUNNEL
TESTING 209 D. REACTION KINETIC STUDIES ON THE SCRAMJET *; . . . . 212
VII. CONCLUSIONS AND FUTURE PROSPECTS 214 ACKNOWLEDGMENTS . 215
REFERENCES 215 CHAPTER 5 SCRAMJET RESEARCH AND DEVELOPMENT IN RUSSIA .
. . . . . 223 I. INTRODUCTION . 223 II. INITIAL STAGE OF SCRAMJET
INVESTIGATIONS (1957-1972) 226 III. SCRAMJET INVESTIGATIONS IN 1972-1996
235 A. TSAGI INVESTIGATIONS 235 B. CIAM INVESTIGATIONS 246 C. ITAM
INVESTIGATIONS 252 D. MAI INVESTIGATIONS 256 IV. SHORT REMARKS ON
SCRAMJET INLET AND NOZZLE DEVELOPMENTS . . . 262 CONTENTS V. CONCLUSION
268 BIBLIOGRAPHY 269 APPENDIX A: THREE PROBLEMS IN SUPERSONIC COMBUSTION
284 A.I. RETARDATION OF HEAT RELEASE IN SUPERSONIC DIVERGING-AREA
COMBUSTOR 284 A. INTRODUCTION . 284 B. FORMULATION 284 C. RESULTS 287
D. QUALITATIVE ANALYSIS OF RESULTS 293 E. CONCLUSIONS 294 REFERENCES 295
A.II. COMBUSTION STABILIZATION IN SUPERSONIC FLOW USING FREE
RECIRCULATING BUBBLE 296 A. INTRODUCTION 296 B. ESTIMATION OF MINIMUM
DIMENSION OF RECIRCULATING BUBBLE NEEDED FOR SELF-IGNITION AND
COMBUSTION STABILIZATION 296 C. SCHEME OF THE EXPERIMENT: FACILITY AND
TESTS CONDITIONS . . . 297 D. EXPERIMENTAL MODEL 298 E. TESTS
METHODOLOGY AND MEASUREMENTS 301 F. EXPERIMENTAL RESULTS 302 G.
CONCLUSIONS 308 ACKNOWLEDGEMENTS 309 REFERENCES 309 A.III. THE
ENHANCEMENT OF LIQUID HYDROCARBON SUPERSONIC COMBUSTION USING
EFFERVESCENT SPRAYS AND INJECTORS WITH NONCIRCULAR NOZZLES 310 A.
INTRODUCTION 310 B. EXPERIMENTAL FACILITY: TEST METHODOLOGY 310 C. TEST
RESULTS :*: 315 D. CONCLUSIONS . . . 319 ACKNOWLEDGMENTS 320
REFERENCES * 320 APPENDIX B: DECELERATION OF SUPERSONIC FLOWS IN
SMOOTHLY DIVERGING-AREA RECTANGULAR DUCTS 321 BIBLIOGRAPHY 337 APPENDIX
C: SOME ASPECTS OF SCRAMJET-VEHICLE INTEGRATION . . . 337 REFERENCES 353
APPENDIX D: LEADING-EDGE BLUNTNESS EFFECT ON PERFORMANCE OF HYPERSONIC
TWO-DIMENSIONAL AIR INTAKES 353 INTRODUCTION 353 ISOLATED
TWO-DIMENSIONAL INTAKE 355 UNDERWRITING INTAKE . 360 REFERENCES 367
CONTENTS XI CHAPTER 6 SCRAMJET PERFORMANCE 369 INTRODUCTION 369 CYCLE
CONSIDERATIONS 373 FLOW NONUNIFORMITY AND CYCLE PERFORMANCE 375 INLET
377 SIDEWALL COMPRESSION CONCEPTS 377 INTERACTIVE INLET DESIGN 381
INLET/ISOLATOR INTERACTIONS 382 COMBUSTOR 386 HYPERSONIC COMBUSTION
PHYSICS 387 SIMULATION REQUIREMENTS 388 EXPERIMENTAL SIMULATION 390
COMPARISON OF COMBUSTION DATA 396 INSTRUMENTATION/MEASUREMENT
REQUIREMENTS 400 COMPUTATIONAL SIMULATION 403 COMPUTATIONAL METHODS 404
COMBUSTOR PERFORMANCE INDEX*THRUST POTENTIAL 409 NOZZLE 412
ENGINE/VEHICLE SYSTEM INTEGRATION 414 FOREBODY/INLET 414
NOZZLE/AFTERBODY 415 CONCLUDING REMARKS 418 APPENDIX A: CENTRAL
INSTITUTE OF AVIATIAN MOTORS NASA MACH 6.5 SCRAMJET FLIGHT TEST 419
INTRODUCTION 419 EXPERIMENTAL APPARATUS AND TEST CONDITIONS 420 FLIGHT
AND GROUND-TEST RESULTS 420 APPENDIX B: NASA S HYPER-X PROGRAM 424
INTRODUCTION 424 FLIGHT-TEST VEHICLE DESIGN AND FABRICATION ... .--. 425
FLIGHT-TEST PLANS 429 HYPER-X TECHNOLOGY 431 ACKNOWLEDGMENTS ,. . . .
439 REFERENCES * * * * 439 CHAPTER 7 SCRAMJET INLETS 447 NOMENCLATURE
447 I. INTRODUCTION 449 II. DEFINITIONS OF PERFORMANCE PARAMETERS 451
III. INLET DESIGN ISSUES 462 A. STARTING AND CONTRACTION LIMITS 462 B.
HIGH-TEMPERATURE EFFECTS 466 C. BLUNT LEADING-EDGE EFFECTS 470 D.
VISCOUS PHENOMENA 477 E. BOUNDARY-LAYER SEPARATION 483 F.
ISOLATORS/SUPERSONIC DIFFUSERS 489 XII CONTENTS G. COMBUSTOR ENTRANCE
PROFILES 489 IV. ENGINE CYCLE CALCULATIONS 489 V. PERFORMANCE
MEASUREMENT TECHNIQUES 492 VI. DESIGN AND PERFORMANCE OF SCRAMJET INLETS
495 A. TWO-DIMENSIONAL PLANAR DESIGNS 495 B. TWO-DIMENSIONAL
AXISYMMETRIC DESIGNS 498 C. THREE-DIMENSIONAL INLET DESIGNS 499 D.
PERFORMANCE CHARACTERISTICS 500 VII. SUMMARY AND RECOMMENDATIONS FOR
FUTURE INVESTIGATIONS . . . 502 REFERENCES 504 CHAPTER 8 SUPERSONIC FLOW
COMBUSTORS 513 NOMENCLATURE 513 I. INTRODUCTION 514 II. PHENOMENOLOGICAL
CONSIDERATIONS 517 A. INLET FLOW 517 B. COMBUSTOR FLOW 521 III. DESIGN
APPROACH IMPLICATIONS 527 A. STEP COMBUSTORS 527 B. ISOLATOR COMBUSTORS
535 IV. FUEL INJECTION BASICS 539 A. WALL JETS 541 B. IN-STREAM
INJECTORS 545 C. HYPERMIXERS 547 D. MIXING 548 V. HIGH MACH NUMBER
IMPLICATIONS 550 A. MIXING 552 B. COMBUSTOR REACTIONS 554 C. CFD
SOLUTION RESULTS =.... : 555 D. DESIGN PHILOSOPHY 561 APPENDIX A: INLET
ONE-DIMENSIONAL CONTINUITY AND ENERGY FLOW SOLUTION 564 APPENDIX B:
PROFILE FLOW SOLUTION 564 APPENDIX C: ENTROPY LIMIT CONCEPT 566
APPENDIX D: COMBUSTOR THRUST POTENTIAL CONCEPT 566 REFERENCES 567
CHAPTER 9 AEROTHERMODYNAMICS OF THE DUAL-MODE COMBUSTION SYSTEM 569
NOMENCLATURE 569 I. INTRODUCTION 570 II. H-K DIAGRAM 571 A. SCRAMJET AND
RAMJET H-K DIAGRAMS 573 B. H-K DIAGRAM CLOSURE 577 III. DUAL-MODE
COMBUSTION SYSTEM 577 A. DUAL-MODE CONCEPT 577 CONTENTS XIII B. RAMJET
MODE (SUBSONIC COMBUSTION) 579 C. SCRAMJET MODE (SUPERSONIC COMBUSTION)
579 D. TRANSITION FROM SCRAMJET TO RAMJET MODE 580 IV. ONE-DIMENSIONAL
FLOW ANALYSIS OF THE ISOLATOR-BURNER SYSTEM . 582 A. CONTROL VOLUME
ANALYSIS OF THE ISOLATOR 583 B. ONE-DIMENSIONAL FLOW ANALYSIS OF THE
BURNER 584 C. ESTABLISHING A CHOKED THERMAL THROAT 5858 V. SYSTEM
ANALYSIS OF ISOLATOR-BURNER INTERACTION . 586 A. SCRAMJET WITH
SHOCK-FREE ISOLATOR 587 B. SCRAMJET WITH OBLIQUE SHOCK TRAIN 587 C.
SCRAMJET WITH NORMAL SHOCK TRAIN 588 VI. INTERPRETATION OF EXPERIMENTAL
DATA 588 A. BILLIG S EXPERIMENTAL WALL-PRESSURE MEASUREMENTS 590 VII.
CLOSURE 593 REFERENCES 594 CHAPTER 10 BASIC PERFORMANCE ASSESSMENT OF
SCRAM COMBUSTORS . . 597 I. INTRODUCTION 597 II. SCRAM-COMBUSTOR
EFFECTIVENESS 600 A. KINETIC ENERGY EFFICIENCY 601 B. ENERGY
AVAILABILITY EFFICIENCY 604 C. STAGNATION PRESSURE EFFICIENCY 606 D.
COMBUSTION PROCESS 607 E. SET OF EFFICIENCIES 607 III. COMPUTATIONAL
TOOL AND LIMITATIONS 609 A. ONE-DIMENSIONAL CALCULATION SCHEME 611 IV.
GENERAL ILLUSTRATIVE STUDIES 613 A. PARAMETRIC STUDIES 613 B. RESULTS
615 V. SPECIFIC ILLUSTRATIVE STUDIES 627 A. HYPERSONIC RESEARCH ENGINE
639 B. DIRECT CONNECT COMBUSTION TESTS DUE TO WALTRUP AND BILLIG (1973)
648 C. NASA LANGLEY DIRECT-CONNECT TESTS DUE TO NORTHAM, GREENBERG,
AND BYINGTON (1989) 654 D. FREE PISTON SHOCK TUNNEL EXPERIMENTS DUE TO
PAULL (1993). . 657 E. TEST DATA DUE TO (1) SABEL NIKOV, VOLOSCHENKO,
OSTRAS, SERMANOV, AND WALTHER (1993) AND (2) MESCHERYAKOV AND
SABEL NIKOV (1981) . . . 657 VI. SCALING PERFORMANCE AND GEOMETRY 667
A. APPROACH 670 B. IGNITION DELAY ESTIMATE 672 C. PRESSURE RISE ALONG
COMBUSTOR 673 VII. COMBUSTOR-BASED SYSTEM INTEGRATION 677 A. INLET AND
NOZZLE EFFICIENCY 677 B. INLET LAYOUT 678 XIV CONTENTS C. NOZZLE LAYOUT
679 REFERENCES 679 APPENDIX A: EFFICIENCY RELATIONS 680 SIMPLE
EFFICIENCY INTERRELATIONS 680 REFERENCES .682 APPENDIX B: HEAT ADDITION
TO A SUPERSONIC GAS FLOW 682 I. CONSTANT PRESSURE HEAT ADDITION IN A
DUCT 682 II. CONSTANT MACH NUMBER HEAT ADDITION IN A DUCT 683 III. HEAT
ADDITION IN A CONSTANT AREA DUCT 683 IV. HEAT ADDITION IN A GENERAL
DIVERGING AREA DUCT 684 V. HEAT ADDITION FOLLOWING A SHOCKWAVE 684 VI.
EFFICIENCIES IN HEAT ADDITION 688 REFERENCES 689 APPENDIX C: HYDROGEN
COMBUSTION SCHEME 689 I. THERMODYNAMIC PROPERTIES 690 II. EQUILIBRIUM
AND NONEQUILIBRIUM COMBUSTION 690 APPENDIX D: THREE-DIMENSIONAL
NOZZLES*DESIGN AND INTEGRATION 693 I. INTERNAL FLOWPATH 693 II.
INTEGRATION WITH THE VEHICLE EXTERNAL FLOW 694 CHAPTER 11 STRUTJET
ROCKET-BASED COMBINED-CYCLE ENGINE 697 I. INTRODUCTION 697 II. STRUTJET
ENGINE 698 A. FLOW-PATH DESCRIPTION 699 B. ENGINE ARCHITECTURE 701 C.
STRUTJET OPERATING MODES 707 D. OPTIMAL PROPULSION SYSTEM SELECTION . .
712 III. STRUTJET ENGINE/VEHICLE INTEGRATION 717 A. STRUTJET REFERENCE
MISSION 717 B. ENGINE-VEHICLE CONSIDERATIONS 720 C. VEHICLE PITCHING
MOMENT 720 D. ENGINE PERFORMANCE 721 E. REDUCED OPERATING COST THROUGH
ROBUSTNESS 722 F. VEHICLE COMPARISONS 729 IV. AVAILABLE HYDROCARBON AND
HYDROGEN TEST DATA AND PLANNED FUTURE TEST ACTIVITIES 733 A. STORABLE
HYDROCARBON SYSTEM TESTS . 734 B. GASEOUS HYDROGEN SYSTEM TESTS . 744 C.
PLANNED FLIGHT TESTS 750 V MATURITY OF REQUIRED STRUTJET TECHNOLOGIES
753 VI. SUMMARY AND CONCLUSIONS 753 A. HYDROGEN AND HYDROCARBON STRUTJET
ENGINES 755 B. STRUTJET TECHNOLOGY MATURITY 755 C. OVERALL
RECOMMENDATION 755 REFERENCES 755 CONTENTS XV CHAPTER 12 LIQUID
HYDROCARBON FUELS FOR HYPERSONIC PROPULSION 757 NOMENCLATURE 757 I.
INTRODUCTION 758 II. FUEL HEAT-SINK REQUIREMENTS AND THE ROLE OF
ENDOTHERMIC FUELS 762 A. CHARACTERISTICS OF ENDOTHERMIC FUELS 763 B.
FUNDAMENTAL CONSIDERATIONS OF HEAT REMOVAL 768 III. FUEL SYSTEM
CHALLENGES 769 A. THERMAL STABILITY 771 B. STRUCTURAL AND HEAT TRANSFER
CONSIDERATIONS 781 C. FUEL-SYSTEM INTEGRATION AND CONTROL 783 IV.
COMBUSTION CHALLENGES 784 A. CHEMICAL KINETIC FOUNDATIONS 788 B. PRESENT
STATE OF CHEMICAL KINETICS 797 C. COMBUSTOR DEVELOPMENT CONSIDERATIONS
800 D. PROSPECTS FOR MODELING LARGE KINETIC SYSTEMS 801 V. SUMMARY 802
ACKNOWLEDGMENTS 802 BIBLIOGRAPHY 802 ADDENDUM*RECENT WORK 813 APPENDIX:
BASIC ELEMENTS OF CHEMICAL KINETIC MECHANISMS . . . 814 THERMOCHEMICAL
AND KINETIC DATABASES 814 CONSTRUCTION AND VALIDATION OF COMPREHENSIVE
COMBUSTION MODELS 815 FORMAL ROUTES TO SENSITIVITY ANALYSES AND
MECHANISM REDUCTION 817 SKELETAL MODELS 820 CHAPTER 13 DETONATION-WAVE
RAMJETS 823 INTRODUCTION 823 EXPERIMENTAL EVIDENCE OF STANDING
DETONATION WAVES . . . . . 828 OPERATING ENVELOPE OF STANDING
DETONATION WAVES ......... 834 FUEL/AIR PREMIXING PROCESS 841
PERFORMANCE ANALYSIS 847 SCRAMJET/AIRFRAME-INTEGRATED WAVERIDER 879
CONCLUDING REMARKS 883 ACKNOWLEDGMENTS 885 REFERENCES :. . 885 CHAPTER
14 PROBLEM OF HYPERSONIC FLOW DECELERATION BY MAGNETIC FIELD 891
INTRODUCTION 891 PECULIARITIES OF MHD CONTROL . 891 REVIEW OF PROPOSALS
TO USE MHD CONTROL . . . 892 XVI CONTENTS CONTENTS OF THE PRESENT
ARTICLE .... . 897 RELATIVE VALUE OF MHD EFFECTS IN HYPERSONIC AIRFLOWS
898 ELECTROCONDUCTIVITY OF AIR AND DIMENSIONLESS MHD PARAMETERS BEHIND A
NORMAL SHOCK WAVE IN A HYPERSONIC FLOW 898 EVALUATION OF CAPABILITIES OF
CONDUCTIVITY INCREASE IN PURE AIR . 899 EQUATIONS OF MAGNETIC GAS
DYNAMICS AT SMALL MAGNETIC REYNOLDS NUMBERS. MAIN PARAMETERS. METHODS OF
NUMERICAL ANALYSIS 901 EQUATIONS OF MAGNETIC GASDYNAMICS AND MAIN
DIMENSIONLESS PARAMETERS 901 PARAMETERS DESCRIBING IRREVERSIBLE LOSSES
IN MHD FLOWS .... 904 MHD DECELERATION OF A HYPERSONIC FLOW IN
ONE-DIMENSIONAL APPROACH 906 NUMERICAL METHOD FOR SOLUTION OF MHD
EQUATION SYSTEM .... 908 BOUNDARY-LAYER SEPARATION PARAMETER IN
MAGNETOGASDYNAMICS 909 PARAMETER OF BOUNDARY-LAYER SEPARATION IN THE
CASE OF NONCONDUCTING WALL 909 PARAMETER OF BOUNDARY-LAYER SEPARATION IN
THE CASE OF CONDUCTING WALL 914 DECELERATION OF A SUPERSONIC FLOW IN A
CIRCULAR NONCONDUCTING TUBE BY AN AXISYMMETRIC MAGNETIC FIELD . . 915
FLOW DECELERATION IN A CIRCULAR TUBE BY MAGNETIC FIELD OF A
SINGLE-CURRENT LOOP 915 FLOW DECELERATION IN A CIRCULAR TUBE BY MAGNETIC
FIELD OF A SOLENOID 922 DECELERATION OF TWO-DIMENSIONAL SUPERSONIC FLOW
IN CHANNELS BY MAGNETIC FIELD PERPENDICULAR TO A FLOW PLANE IN GENERATOR
REGIME 928 FORMULATION OF A PROBLEM - - : - 928 QUASI-ONE-DIMENSIONAL
APPROXIMATION FOR ELECTRICAL VARIABLES 930 NUMERICAL ANALYSIS OF LAMINAR
AND TURBULENT FLOWS ........ 932 CONCLUSIONS ,.... 934 REFERENCES 936
CHAPTER 15 RUDIMENTS AND METHODOLOGY FOR DESIGN AND ANALYSIS OF
HYPERSONIC AIRBREATHING VEHICLES 939 INTRODUCTION . 939 RUDIMENTS OF
DESIGN 941 COORDINATE SYSTEM 941 FORCE ACCOUNTING SYSTEM 942 NOMINAL
SSTO VEHICLE/TRAJECTORY 945 LOADS 946 STABILITY AND CONTROL . 948
REPRESENTATIVE FORCES AND MOMENTS 950 CONTENTS XVII IMPACT OF PROPULSION
LIFT ON AERODYNAMICS 952 ENGINE/AIRFRAME INTEGRATION METHODOLOGY 956
ENGINEERING METHODS 957 HIGHER-ORDER NUMERICAL METHODS 966 VEHICLE
DESIGN METHODOLOGY 968 AERODYNAMICS/AEROTHERMODYNAMICS .969
STRUCTURES/TPS SIZING 969 CLOSURE 971 VEHICLE PERFORMANCE 971
SYNTHESIS/SIZING 972 DESIGN AUTOMATION/OPTIMIZATION 972 SUMMARY 975
ACKNOWLEDGMENTS 975 REFERENCES 975 CHAPTER 16 TRANSATMOSPHERIC LAUNCHER
SIZING 979 NOMENCLATURE 979 I. INTRODUCTION 982 A. THEME 982 B.
OBJECTIVES 983 II. VEHICLE SIZING APPROACH 983 A. APPROACH 984 B. SIZING
METHODOLOGY 985 C. FUNDAMENTAL SIZING RELATIONSHIPS 987 D. EFFECT OF R
ON CONFIGURATION CONCEPTS 989 E. PARAMETRIC SIZING INTERACTIONS 989 F.
SUMMARY OF PARAMETER GROUPS 990 G. EXTERNAL AERODYNAMICS 992 H.
TECHNOLOGY MATURITY DETERMINATION 994 III. PROPULSION SYSTEMS 996 A.
PERFORMANCE CHARACTERISTICS OF AIR BREATHING ENGINES .... 997 B. MAJOR
SEQUENCE OF PROPULSION CYCLES 1000 C. CYCLE COMPARISON *-.... 1007 IV.
SIZING CODE 1011 A. HYPERSONIC CONVERGENCE SIZING CODE 1011 B. FINAL
HYPERSONIC CONVERGENCE RELATIONSHIPS 1012 C. VANDENKERCKHOVE SIZING CODE
1014 V. VDK SIZING APPROACH 1014 A. WEIGHT BUDGET . 1016 B. VOLUME
BUDGET 1018 C. INPUT VALUES ASSUMPTIONS 1019 D. VOLUME AND WEIGHT
ASSUMPTIONS 1020 E. AERODYNAMICS : 1021 F. PROPULSION 1021 G.
TRAJECTORY 1022 VI. SSTO LAUNCHER SIZING 1022 XVIII CONTENTS A.
DETERMINATION OF VEHICLE LENGTH 1023 B. DESIGN 1026 C. MISSION 1039 D.
GEOMETRY 1043 E. STRONG PARAMETER CROSS-COUPLINGS 1048 VII. TSTO
LAUNCHER SIZING 1051 A. ASSUMPTIONS 1052 B. VOLUME AND WEIGHTS 1053 C.
PROPULSION 1053 D. AERODYNAMICS 1053 E. TRAJECTORY 1054 F. FIRST STAGE
1054 G. SECOND STAGE 1056 H. TSTO SIZING RESULTS 1057 I. INFLUENCE OF
FIRST STAGE PROPULSION CONCEPT 1058 J. DISCUSSION OF RESULTS 1058 VIII.
COMPARISON BETWEEN SSTO AND TSTO 1059 IX. AIR LIQUEFACTION AND LOX
COLLECTION 1063 A. PROPULSION SYSTEM CONFIGURATION 1063 B. SIZING MODEL
MODIFICATIONS AND ASSUMPTIONS 1065 C. APPLICATION TO SSTO 1067 D.
APPLICATION TO TSTO 1072 E. SUMMARY 1072 X. CONCLUSIONS 1075 REFERENCES
1076 APPENDIX A: HYPERSONIC CONFIGURATION GEOMETRIC CHARACTERISTICS 1084
APPENDIX B: IMPACT OF LOWER SPEED THRUST MINUS DRAG .... 1088 PROPULSION
AIRFRAME STRONG INTERACTIONS 1089 REFERENCES *-.-. 1091 APPENDIX B:
IMPACT OF LOWER SPEED THRUST MINUS DRAG .... 1095 PROPULSION AIRFRAME
STRONG INTERACTIONS 1097 REFERENCES 1103 CHAPTER 17 SCRAMJET FLOWPATH
INTEGRATION 1105 I. BACKGROUND 1105 A. SCRAMJET-POWERED VEHICLES 1105 B.
FLOWPATH OPTIMIZATION 1112 II. ENERGY ANALYSIS . 1117 A. HYPERSONIC
ENERGY PARTITIONING 1119 B. SUMMARY AND STATEMENT OF THE DESIGN PROBLEM
1122 III. INLET : . 1124 A. SOME USEFUL DIRECT RELATIONS 1125 B.
FLOWFIELD IN THE INLET FLOWPATH INTRODUCES DISTORTION PARAMETERS 1127 C.
DETERMINATION OF # WP 1129 CONTENTS XIX D. INLET TESTING AND
DETERMINATION OF /C WP 1130 E. IMPLICATIONS OF THERMODYNAMIC ANALYSIS TO
DESIGN OF INLETS 1132 IV. FOREBODY 1134 A. FOREBODY DESIGN 1134 B. INLET
FOREBODY INTEGRATION 1137 V. FORCE ACCOUNTING 1140 A. FORCE ACCOUNTING
VIEWPOINT 1138 B. LIFT DRAG 1150 C. FLOW TURNING AND OVERALL DESIGN OF
INLET 1152 D. FORCE ACCOUNTING APPROACHES 1158 VI. COMBUSTOR 1158 A.
ISOLATOR 1159 B. DUAL-MODE COMBUSTOR ISOLATOR 1161 C. DETONATION WAVE
ENGINE 1168 D. APPLICATION TO A DUAL-MODE COMBUSTOR 1169 E. SCRAMJET
1177 F. FRICTION CYCLE 1181 G. STEP COMBUSTOR , 1190 H. SUMMARY 1196
VII. NOZZLE COMPONENT LOSSES 1196 A. STANDARD LOSS CATEGORIES 1197 B.
EXPANSION PROCESS PHYSICS 1198 VIII. INTEGRATION RESULTS 1201 A.
PARTITIONING OF INTERNAL FLOWPATH 1201 B. ENGINE MODULE FLOWPATH
INTEGRATION 1202 C. SCRAMJET INTEGRATION AND EXAMPLE 1204 D. VEHICLE
MASS PROPERTIES 1204 E. MASS FRACTION REQUIRED 1205 F. CLOSURE -. . :
1208 IX. SUMMARY AND RECOMMENDATIONS 1213 BIBLIOGRAPHY 1216 APPENDIX A:
DYNAMICS OF A FLIGHT VEHICLE 1218 A. CRUISE FLIGHT 1218 B. ACCELERATED
FLIGHT 1219 C. APPLICATION TO A CONSTANT I SP ENGINE 1219 D. APPLICATION
TO A CONSTANT V-I SP ENGINE 1220 APPENDIX B: BRAYTON CYCLE SCRAMJET 1221
APPENDIX C: AEROTHERMODYNAMICS OF SCRAMJET ENGINE 1222 A. PRESSURE
COEFFICIENT 1222 B. ENGINE CYCLE THERMODYNAMIC FUNCTIONS 1224 C.
BOUNDARY-LAYER INFLUENCE 1226 D. EXPERIMENTAL DETERMINATION OF INLET K
WP 1232 E. RATIO OF SPECIFIC HEATS FOR AIR 1236 F. FURTHER ANALYSIS OF
THERMAL RATIO 1238 APPENDIX D: HYPERSONIC SLENDER BODY THEORY APPLIED TO
FOREBODIES AND LEADING EDGES 1240 XX CONTENTS A. FOREBODIES 1240 B.
LEADING EDGES 1243 C. CASE OF UNEQUAL ANGLES 1244 D. OVERSPEED SITUATION
IN AN INLET 1245 APPENDIX E: SCALING DRAG AND HEAT TRANSFER 1249 A.
SKIN-FRICTION COEFFICIENT 1249 B. HEAT TRANSFER 1252 APPENDIX F: FORCE
ACCOUNTING PROCEDURES 1254 A. FREESTREAM FORCE ACCOUNTING 1257 B.
COWL-TO-TAIL ACCOUNTING 1257 C. LIFT EFFECTS 1257 APPENDIX G: GEOMETRY
AND MASS OF INTEGRATED VEHICLE .... 1258 A. GEOMETRY 1258 B. WEIGHT
ANALYSIS 1262 APPENDIX H: TWO-WAVE COMBUSTION MODEL FOR OPTIMAL
SUPERSONIC COMBUSTION PERFORMANCE 1269 A. HEAT ADDITION IN A DUAL-MODE
COMBUSTOR 1269 B. SCRAMJET TWO-WAVE COMBUSTOR 1275 APPENDIX I: BASE
PRESSURE ESTIMATE 1280 A. REQUIRED PRESSURE AT REATTACHMENT 1280 B.
CLOSURE 1289 NOMENCLATURE FOR FLOW PATH COMPONENT SPECIFICATION 1290
|
| any_adam_object | 1 |
| building | Verbundindex |
| bvnumber | BV013813106 |
| callnumber-first | T - Technology |
| callnumber-label | TL507 |
| callnumber-raw | TL507 |
| callnumber-search | TL507 |
| callnumber-sort | TL 3507 |
| callnumber-subject | TL - Motor Vehicles and Aeronautics |
| classification_tum | VER 636f VER 516f MAS 590f |
| ctrlnum | (OCoLC)46734717 (DE-599)BVBBV013813106 |
| dewey-full | 629.1 629.134/3535 |
| dewey-hundreds | 600 - Technology (Applied sciences) |
| dewey-ones | 629 - Other branches of engineering |
| dewey-raw | 629.1 629.134/3535 |
| dewey-search | 629.1 629.134/3535 |
| dewey-sort | 3629.1 |
| dewey-tens | 620 - Engineering and allied operations |
| discipline | Verkehrstechnik Verkehr / Transport Maschinenbau |
| format | Book |
| fullrecord | <?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>02397nam a2200577 cb4500</leader><controlfield tag="001">BV013813106</controlfield><controlfield tag="003">DE-604</controlfield><controlfield tag="005">20010711 </controlfield><controlfield tag="007">t</controlfield><controlfield tag="008">010710s2000 ad|| |||| 00||| eng d</controlfield><datafield tag="020" ind1=" " ind2=" "><subfield code="a">1563473224</subfield><subfield code="9">1-56347-322-4</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(OCoLC)46734717</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-599)BVBBV013813106</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-604</subfield><subfield code="b">ger</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1="0" ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="049" ind1=" " ind2=" "><subfield code="a">DE-91G</subfield><subfield code="a">DE-706</subfield><subfield code="a">DE-634</subfield><subfield code="a">DE-83</subfield></datafield><datafield tag="050" ind1=" " ind2="0"><subfield code="a">TL507</subfield></datafield><datafield tag="082" ind1="0" ind2=" "><subfield code="a">629.1</subfield><subfield code="2">21</subfield></datafield><datafield tag="082" ind1="0" ind2=" "><subfield code="a">629.134/3535</subfield><subfield code="2">21</subfield></datafield><datafield tag="084" ind1=" " ind2=" "><subfield code="a">VER 636f</subfield><subfield code="2">stub</subfield></datafield><datafield tag="084" ind1=" " ind2=" "><subfield code="a">VER 516f</subfield><subfield code="2">stub</subfield></datafield><datafield tag="084" ind1=" " ind2=" "><subfield code="a">MAS 590f</subfield><subfield code="2">stub</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Scramjet propulsion</subfield><subfield code="c">ed. by E. T. Curran ...</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="a">Reston</subfield><subfield code="b">American Institute of Aeronautics and Astronautics</subfield><subfield code="c">2000</subfield></datafield><datafield tag="300" ind1=" " ind2=" "><subfield code="a">XXVII, 1293 S.</subfield><subfield code="b">Ill., graph. Darst.</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="b">n</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="b">nc</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="490" ind1="1" ind2=" "><subfield code="a">Progress in astronautics and aeronautics</subfield><subfield code="v">189</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Avions - Statoréacteurs à combustion supersonique</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Propulsion par réaction</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Airplanes</subfield><subfield code="x">Scramjet engines</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Jet propulsion</subfield></datafield><datafield tag="650" ind1="0" ind2="7"><subfield code="a">Raumfahrzeug</subfield><subfield code="0">(DE-588)4048579-1</subfield><subfield code="2">gnd</subfield><subfield code="9">rswk-swf</subfield></datafield><datafield tag="650" ind1="0" ind2="7"><subfield code="a">Raketentriebwerk</subfield><subfield code="0">(DE-588)4176905-3</subfield><subfield code="2">gnd</subfield><subfield code="9">rswk-swf</subfield></datafield><datafield tag="650" ind1="0" ind2="7"><subfield code="a">Überschallstaustrahltriebwerk</subfield><subfield code="0">(DE-588)4427457-9</subfield><subfield code="2">gnd</subfield><subfield code="9">rswk-swf</subfield></datafield><datafield tag="650" ind1="0" ind2="7"><subfield code="a">Überschallflugzeug</subfield><subfield code="0">(DE-588)4186622-8</subfield><subfield code="2">gnd</subfield><subfield code="9">rswk-swf</subfield></datafield><datafield tag="650" ind1="0" ind2="7"><subfield code="a">Hyperschallbereich</subfield><subfield code="0">(DE-588)4161092-1</subfield><subfield code="2">gnd</subfield><subfield code="9">rswk-swf</subfield></datafield><datafield tag="650" ind1="0" ind2="7"><subfield code="a">Luftstrahltriebwerk</subfield><subfield code="0">(DE-588)4128278-4</subfield><subfield code="2">gnd</subfield><subfield code="9">rswk-swf</subfield></datafield><datafield tag="689" ind1="0" ind2="0"><subfield code="a">Raumfahrzeug</subfield><subfield code="0">(DE-588)4048579-1</subfield><subfield code="D">s</subfield></datafield><datafield tag="689" ind1="0" ind2="1"><subfield code="a">Raketentriebwerk</subfield><subfield code="0">(DE-588)4176905-3</subfield><subfield code="D">s</subfield></datafield><datafield tag="689" ind1="0" ind2="2"><subfield code="a">Überschallflugzeug</subfield><subfield code="0">(DE-588)4186622-8</subfield><subfield code="D">s</subfield></datafield><datafield tag="689" ind1="0" ind2="3"><subfield code="a">Luftstrahltriebwerk</subfield><subfield code="0">(DE-588)4128278-4</subfield><subfield code="D">s</subfield></datafield><datafield tag="689" ind1="0" ind2="4"><subfield code="a">Überschallstaustrahltriebwerk</subfield><subfield code="0">(DE-588)4427457-9</subfield><subfield code="D">s</subfield></datafield><datafield tag="689" ind1="0" ind2="5"><subfield code="a">Hyperschallbereich</subfield><subfield code="0">(DE-588)4161092-1</subfield><subfield code="D">s</subfield></datafield><datafield tag="689" ind1="0" ind2=" "><subfield code="8">1\p</subfield><subfield code="5">DE-604</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Curran, E. T.</subfield><subfield code="e">Sonstige</subfield><subfield code="4">oth</subfield></datafield><datafield tag="830" ind1=" " ind2="0"><subfield code="a">Progress in astronautics and aeronautics</subfield><subfield code="v">189</subfield><subfield code="w">(DE-604)BV001890233</subfield><subfield code="9">189</subfield></datafield><datafield tag="856" ind1="4" ind2="2"><subfield code="m">GBV Datenaustausch</subfield><subfield code="q">application/pdf</subfield><subfield code="u">http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&local_base=BVB01&doc_number=009444379&sequence=000001&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA</subfield><subfield code="3">Inhaltsverzeichnis</subfield></datafield><datafield tag="999" ind1=" " ind2=" "><subfield code="a">oai:aleph.bib-bvb.de:BVB01-009444379</subfield></datafield><datafield tag="883" ind1="1" ind2=" "><subfield code="8">1\p</subfield><subfield code="a">cgwrk</subfield><subfield code="d">20201028</subfield><subfield code="q">DE-101</subfield><subfield code="u">https://d-nb.info/provenance/plan#cgwrk</subfield></datafield></record></collection> |
| id | DE-604.BV013813106 |
| illustrated | Illustrated |
| indexdate | 2024-07-09T18:52:25Z |
| institution | BVB |
| isbn | 1563473224 |
| language | English |
| oai_aleph_id | oai:aleph.bib-bvb.de:BVB01-009444379 |
| oclc_num | 46734717 |
| open_access_boolean | |
| owner | DE-91G DE-BY-TUM DE-706 DE-634 DE-83 |
| owner_facet | DE-91G DE-BY-TUM DE-706 DE-634 DE-83 |
| physical | XXVII, 1293 S. Ill., graph. Darst. |
| publishDate | 2000 |
| publishDateSearch | 2000 |
| publishDateSort | 2000 |
| publisher | American Institute of Aeronautics and Astronautics |
| record_format | marc |
| series | Progress in astronautics and aeronautics |
| series2 | Progress in astronautics and aeronautics |
| spelling | Scramjet propulsion ed. by E. T. Curran ... Reston American Institute of Aeronautics and Astronautics 2000 XXVII, 1293 S. Ill., graph. Darst. txt rdacontent n rdamedia nc rdacarrier Progress in astronautics and aeronautics 189 Avions - Statoréacteurs à combustion supersonique Propulsion par réaction Airplanes Scramjet engines Jet propulsion Raumfahrzeug (DE-588)4048579-1 gnd rswk-swf Raketentriebwerk (DE-588)4176905-3 gnd rswk-swf Überschallstaustrahltriebwerk (DE-588)4427457-9 gnd rswk-swf Überschallflugzeug (DE-588)4186622-8 gnd rswk-swf Hyperschallbereich (DE-588)4161092-1 gnd rswk-swf Luftstrahltriebwerk (DE-588)4128278-4 gnd rswk-swf Raumfahrzeug (DE-588)4048579-1 s Raketentriebwerk (DE-588)4176905-3 s Überschallflugzeug (DE-588)4186622-8 s Luftstrahltriebwerk (DE-588)4128278-4 s Überschallstaustrahltriebwerk (DE-588)4427457-9 s Hyperschallbereich (DE-588)4161092-1 s 1\p DE-604 Curran, E. T. Sonstige oth Progress in astronautics and aeronautics 189 (DE-604)BV001890233 189 GBV Datenaustausch application/pdf http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&local_base=BVB01&doc_number=009444379&sequence=000001&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA Inhaltsverzeichnis 1\p cgwrk 20201028 DE-101 https://d-nb.info/provenance/plan#cgwrk |
| spellingShingle | Scramjet propulsion Progress in astronautics and aeronautics Avions - Statoréacteurs à combustion supersonique Propulsion par réaction Airplanes Scramjet engines Jet propulsion Raumfahrzeug (DE-588)4048579-1 gnd Raketentriebwerk (DE-588)4176905-3 gnd Überschallstaustrahltriebwerk (DE-588)4427457-9 gnd Überschallflugzeug (DE-588)4186622-8 gnd Hyperschallbereich (DE-588)4161092-1 gnd Luftstrahltriebwerk (DE-588)4128278-4 gnd |
| subject_GND | (DE-588)4048579-1 (DE-588)4176905-3 (DE-588)4427457-9 (DE-588)4186622-8 (DE-588)4161092-1 (DE-588)4128278-4 |
| title | Scramjet propulsion |
| title_auth | Scramjet propulsion |
| title_exact_search | Scramjet propulsion |
| title_full | Scramjet propulsion ed. by E. T. Curran ... |
| title_fullStr | Scramjet propulsion ed. by E. T. Curran ... |
| title_full_unstemmed | Scramjet propulsion ed. by E. T. Curran ... |
| title_short | Scramjet propulsion |
| title_sort | scramjet propulsion |
| topic | Avions - Statoréacteurs à combustion supersonique Propulsion par réaction Airplanes Scramjet engines Jet propulsion Raumfahrzeug (DE-588)4048579-1 gnd Raketentriebwerk (DE-588)4176905-3 gnd Überschallstaustrahltriebwerk (DE-588)4427457-9 gnd Überschallflugzeug (DE-588)4186622-8 gnd Hyperschallbereich (DE-588)4161092-1 gnd Luftstrahltriebwerk (DE-588)4128278-4 gnd |
| topic_facet | Avions - Statoréacteurs à combustion supersonique Propulsion par réaction Airplanes Scramjet engines Jet propulsion Raumfahrzeug Raketentriebwerk Überschallstaustrahltriebwerk Überschallflugzeug Hyperschallbereich Luftstrahltriebwerk |
| url | http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&local_base=BVB01&doc_number=009444379&sequence=000001&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA |
| volume_link | (DE-604)BV001890233 |
| work_keys_str_mv | AT curranet scramjetpropulsion |