Scramjet propulsion

Supersonic combustion ramjet (SCRJ) engine research and development begun some 40 years ago is the key to airbreathing hypersonic flight. Many unexpected complexities of SCRJ engine combustion and combustor-inlet interaction have been continuing challenges. However, valuable progress has been made in several aspects. In the next few years, it would appear that significant flight testing will take place in several countries and this should lead to further understanding of SCRJ processes in engine design for cruise and accelerator vehicle applications. This volume - the third and final in a mini-series on hypersonic propulsion along with High Speed Flight Propulsion Systems, volume 137, and Developments in High Speed Flight Propulsion Systems, volume 165 - presents a comprehensive and detailed exposition of the gradual maturing of scramjet technologies. Developments in several parts of the world are described by those intimately involved in the main stream of SCRJ activities. It is clear that fresh opportunities exist to improve the robustness of high-speed-fight propulsion, and this book offers a timely lead to a new entrant to this technology as well as new insights to specialists.

Preface	p. xxi
Introduction	p. xxiii
I. International Efforts	p. xxiii
II. Inlets, Combustors, and Fuels	p. xxiv
III. Overall Systems	p. xxiv
IV. Future Developments	p. xxv
V. Closing Comments	p. xxv
References	p. xxvi
Chapter 1 Scramjet Testing in the T3 and T4 Hypersonic Impulse Facilities	p. 1
Nomenclature	p. 1
I. History, Aims, and Developments	p. 2
II. Facility and Instrumentation	p. 5
III. Fuel-Injection Systems	p. 6
IV. Combustion/Mixing Processes	p. 17
V. Simple Theoretical Combustor and Thrust Model	p. 21
VI. Experimental Results of Specific Impulse	p. 25
VII. Effects of Atomic Oxygen and Nitric Oxide in the Freestream	p. 30
VIII. Different Fuels	p. 32
IX. Integrated Scramjet Measurements	p. 35
X. Skin-Friction Measurements	p. 40
XI. Discussion and Review	p. 42
Acknowledgments	p. 43
Bibliography	p. 43
Chapter 2 Scramjet Developments in France	p. 47
I. Historical Overview	p. 47
II. Basic Research on Diffusion Flame Combustion (1962-1967)	p. 49
III. ESOPE Program (1966-1973)	p. 59
IV. Studies on Shock-Induced Combustion	p. 81
V. Prepha Program (1992-1997)	p. 84
VI. Perspectives	p. 103
References	p. 112
Chapter 3 Scramjet Investigations Within the German Hypersonics Technology Program (1993-1996)	p. 119
I. German Hypersonics Technology Program and Scramjet-Related Activities	p. 119
II. Theoretical Investigations for Scramjet Intake Designs	p. 121
III. Theoretical and Experimental Investigations of Scramjet Combustion at TsAGI and DLR Lampoldshausen	p. 137
IV. Freejet Wind-tunnel Testing of Scramjet Propulsion Systems at TsAGI	p. 144
V. Considerations for Flight Testing Small-Scale Scramjet Modules Using the RADUGA-D2 Flying Testbed	p. 149
References	p. 158
Chapter 4 Scramjet Engine Research at the National Aerospace Laboratory in Japan	p. 159
Nomenclature	p. 159
I. Introduction	p. 160
II. Engine Model	p. 161
III. Test Facility	p. 170
IV. Measurements	p. 177
V. 5 Test Results	p. 179
VI. Supplementary Studies for Engine Testing	p. 203
VII. Conclusions and Future Prospects	p. 214
Acknowledgments	p. 215
References	p. 215
Chapter 5 Scramjet Research and Development in Russia	p. 223
I. Introduction	p. 223
II. Initial Stage of Scramjet Investigations (1957-1972)	p. 226
III. Scramjet Investigations in 1972-1996	p. 235
IV. Short Remarks on Scramjet Inlet and Nozzle Developments	p. 262
V. Conclusion	p. 268
Bibliography	p. 269
Appendix A Three Problems in Supersonic Combustion	p. 284
Appendix B Deceleration of Supersonic Flows in Smoothly Diverging-Area Rectangular Ducts	p. 321
Appendix C Some Aspects of Scramjet-Vehicle Integration	p. 337
Appendix D Leading-Edge Bluntness Effect on Performance of Hypersonic Two-Dimensional Air Intakes	p. 353
Chapter 6 Scramjet Performance	p. 369
Introduction	p. 369
Cycle Considerations	p. 373
Flow Nonuniformity and Cycle Performance	p. 375
Inlet	p. 377
Sidewall Compression Concepts	p. 377
Interactive Inlet Design	p. 381
Inlet/Isolator Interactions	p. 382
Combustor	p. 386
Hypersonic Combustion Physics	p. 387
Simulation Requirements	p. 388
Experimental Simulation	p. 390
Comparison of Combustion Data	p. 396
Instrumentation/Measurement Requirements	p. 400
Computational Simulation	p. 403
Computational Methods	p. 404
Combustor Performance Index--Thrust Potential	p. 409
Nozzle	p. 412
Engine/Vehicle System Integration	p. 414
Forebody/Inlet	p. 414
Nozzle/Afterbody	p. 415
Concluding Remarks	p. 418
Appendix A Central Institute of Aviation Motors NASA MACH 6.5 Scramjet Flight Test	p. 419
Introduction	p. 419
Experimental Apparatus and Test Conditions	p. 420
Flight and Ground-Test Results	p. 420
Appendix B NASA'S Hyper-X Program	p. 424
Introduction	p. 424
Flight-Test Vehicle Design and Fabrication	p. 425
Flight-Test Plans	p. 429
Hyper-X Technology	p. 431
Acknowledgments	p. 439
References	p. 439
Chapter 7 Scramjet Inlets	p. 447
Nomenclature	p. 447
I. Introduction	p. 449
II. Definitions of Performance Parameters	p. 451
III. Inlet Design Issues	p. 462
IV. Engine Cycle Calculations	p. 489
V. Performance Measurement Techniques	p. 492
VI. Design and Performance of Scramjet Inlets	p. 495
VII. Summary and Recommendations for Future Investigations	p. 502
References	p. 504
Chapter 8 Supersonic Flow Combustors	p. 513
Nomenclature	p. 513
I. Introduction	p. 514
II. Phenomenological Considerations	p. 517
III. Design Approach Implications	p. 527
IV. Fuel Injection Basics	p. 539
V. High Mach Number Implications	p. 550
Appendix A Inlet One-Dimensional Continuity and Energy Flow Solution	p. 564
Appendix B Profile Flow Solution	p. 564
Appendix C Entropy Limit Concept	p. 566
Appendix D Combustor Thrust Potential Concept	p. 566
References	p. 567
Chapter 9 Aerothermodynamics of the Dual-Mode Combustion System	p. 569
Nomenclature	p. 569
I. Introduction	p. 570
II. H-K Diagram	p. 571
III. Dual-Mode Combustion System	p. 577
IV. One-Dimensional Flow Analysis of the Isolator-Burner System	p. 582
V. System Analysis of Isolator-Burner Interaction	p. 586
VI. Interpretation of Experimental Data	p. 588
VII. Closure	p. 593
References	p. 594
Chapter 10 Basic Performance Assessment of Scram Combustors	p. 597
I. Introduction	p. 597
II. Scram-Combustor Effectiveness	p. 600
III. Computational Tool and Limitations	p. 609
IV. General Illustrative Studies	p. 613
V. Specific Illustrative Studies	p. 627
VI. Scaling Performance and Geometry	p. 667
VII. Combustor-Based System Integration	p. 677
References	p. 679
Appendix A Efficiency Relations	p. 680
Appendix B Heat Addition to a Supersonic Gas Flow	p. 682
I. Constant Pressure Heat Addition in a Duct	p. 682
II. Constant Mach Number Heat Addition in a Duct	p. 683
III. Heat Addition in a Constant Area Duct	p. 683
IV. Heat Addition in a General Diverging Area Duct	p. 684
V. Heat Addition Following a Shockwave	p. 684
VI. Efficiencies in Heat Addition	p. 688
Appendix C Hydrogen Combustion Scheme	p. 689
I. Thermodynamic Properties	p. 690
II. Equilibrium and Nonequilibrium Combustion	p. 690
Appendix D Three-Dimensional Nozzles--Design and Integration	p. 693
I. Internal Flowpath	p. 693
II. Integration with the Vehicle External Flow	p. 694
Chapter 11 Strutjet Rocket-Based Combined-Cycle Engine	p. 697
I. Introduction	p. 697
II. Strutjet Engine	p. 698
III. Strutjet Engine/Vehicle Integration	p. 717
IV. Available Hydrocarbon and Hydrogen Test Data and Planned Future Test Activities	p. 733
V. Maturity of Required Strutjet Technologies	p. 753
VI. Summary and Conclusions	p. 753
References	p. 755
Chapter 12 Liquid Hydrocarbon Fuels for Hypersonic Propulsion	p. 757
Nomenclature	p. 757
I. Introduction	p. 758
II. Fuel Heat-Sink Requirements and the Role of Endothermic Fuels	p. 762
III. Fuel System Challenges	p. 769
IV. Combustion Challenges	p. 784
V. Summary	p. 802
Acknowledgments	p. 802
Bibliography	p. 802
Addendum--Recent Work	p. 813
Appendix Basic Elements of Chemical Kinetic Mechanisms	p. 814
Thermochemical and Kinetic Databases	p. 814
Construction and Validation of Comprehensive Combustion Models	p. 815
Formal Routes to Sensitivity Analyses and Mechanism Reduction	p. 817
Skeletal Models	p. 820
Chapter 13 Detonation-Wave Ramjets	p. 823
Introduction	p. 823
Experimental Evidence of Standing Detonation Waves	p. 828
Operating Envelope of Standing Detonation Waves	p. 834
Fuel/Air Premixing Process	p. 841
Performance Analysis	p. 847
Scramjet/Airframe-Integrated Waverider	p. 879
Concluding Remarks	p. 883
Acknowledgments	p. 885
References	p. 885
Chapter 14 Problem of Hypersonic Flow Deceleration by Magnetic Field	p. 891
Introduction	p. 891
Peculiarities of MHD Control	p. 891
Review of Proposals to Use MHD Control	p. 892
Contents of the Present Article	p. 897
Relative Value of MHD Effects in Hypersonic Airflows	p. 898
Electroconductivity of Air and Dimensionless MHD Parameters Behind a Normal Shock Wave in a Hypersonic Flow	p. 898
Evaluation of Capabilities of Conductivity Increase in Pure Air	p. 899
Equations of Magnetic Gas Dynamics at Small Magnetic Reynolds Numbers. Main Parameters. Methods of Numerical Analysis	p. 901
Equations of Magnetic Gasdynamics and Main Dimensionless Parameters	p. 901
Parameters Describing Irreversible Losses in MHD Flows	p. 904
MHD Deceleration of a Hypersonic Flow in One-Dimensional Approach	p. 906
Numerical Method for Solution of MHD Equation System	p. 908
Boundary-Layer Separation Parameter in Magnetogasdynamics	p. 909
Parameter of Boundary-Layer Separation in the Case of Nonconducting Wall	p. 909
Parameter of Boundary-Layer Separation in the Case of Conducting Wall	p. 914
Deceleration of a Supersonic Flow in a Circular Nonconducting Tube by an Axisymmetric Magnetic Field	p. 915
Flow Deceleration in a Circular Tube by Magnetic Field of a Single-Current Loop	p. 915
Flow Deceleration in a Circular Tube by Magnetic Field of a Solenoid	p. 922
Deceleration of Two-Dimensional Supersonic Flow in Channels by Magnetic Field Perpendicular to a Flow Plane In Generator Regime	p. 928
Formulation of a Problem	p. 928
Quasi-One-Dimensional Approximation for Electrical Variables	p. 930
Numerical Analysis of Laminar and Turbulent Flows	p. 932
Conclusions	p. 934
References	p. 936
Chapter 15 Rudiments and Methodology for Design and Analysis of Hypersonic Airbreathing Vehicles	p. 939
Introduction	p. 939
Rudiments of Design	p. 941
Coordinate System	p. 941
Force Accounting System	p. 942
Nominal SSTO Vehicle/Trajectory	p. 945
Loads	p. 946
Stability and Control	p. 948
Representative Forces and Moments	p. 950
Impact of Propulsion Lift on Aerodynamics	p. 952
Engine/Airframe Integration Methodology	p. 956
Engineering Methods	p. 957
Higher-Order Numerical Methods	p. 966
Vehicle Design Methodology	p. 968
Aerodynamics/Aerothermodynamics	p. 969
Structures/TPS Sizing	p. 969
Closure	p. 971
Vehicle Performance	p. 971
Synthesis/Sizing	p. 972
Design Automation/Optimization	p. 972
Summary	p. 975
Acknowledgments	p. 975
References	p. 975
Chapter 16 Transatmospheric Launcher Sizing	p. 979
Nomenclature	p. 979
I. Introduction	p. 982
II. Vehicle Sizing Approach	p. 983
III. Propulsion Systems	p. 996
IV. Sizing Code	p. 1011
V. VDK Sizing Approach	p. 1014
VI. SSTO Launcher Sizing	p. 1022
VII. TSTO Launcher Sizing	p. 1051
VIII. Comparison Between SSTO and TSTO	p. 1059
IX. Air Liquefaction and LOX Collection	p. 1063
X. Conclusions	p. 1075
References	p. 1076
Appendix A Hypersonic Configuration Geometric Characteristics	p. 1084
Appendix B Impact of Lower Speed Thrust Minus Drag	p. 1088
Chapter 17 Scramjet Flowpath Integration	p. 1105
I. Background	p. 1105
II. Energy Analysis	p. 1117
III. Inlet	p. 1124
IV. Forebody	p. 1134
V. Force Accounting	p. 1140
VI. Combustor	p. 1158
VII. Nozzle Component Losses	p. 1196
VIII. Integration Results	p. 1201
IX. Summary and Recommendations	p. 1213
Bibliography	p. 1216
Appendix A Dynamics of a Flight Vehicle	p. 1218
Appendix B Brayton Cycle Scramjet	p. 1221
Appendix C Aerothermodynamics of Scramjet Engine	p. 1222
Appendix D Hypersonic Slender Body Theory Applied to Forebodies and Leading Edges	p. 1240
Appendix E Scaling Drag and Heat Transfer	p. 1249
Appendix F Force Accounting Procedures	p. 1254
Appendix G Geometry and Mass of Integrated Vehicle	p. 1258
Appendix H Two-Wave Combustion Model for Optimal Supersonic Combustion Performance	p. 1269
Appendix I Base Pressure Estimate	p. 1280
Nomenclature for Flow Path Component Specification	p. 1290

Available:*

On Order

Summary

Summary

Table of Contents