This chapter contains sections titled:

    PDF/FDF‐Methods for the Prediction of Supersonic Turbulent Combustion

    Introduction

    Methods for Turbulent Reacting Flow Calculations

    Basic Methods

    Hybrid PDF/FDF‐Methods

    Some Deficiencies of Existing Hybrid PDF‐Methods

    The Transport Problem

    The Mixing Problem

    The Energy Problem

    New Theoretical Concepts

    The Transport Problem

    The Mixing Problem

    The Energy Problem

    The Use of PDF Combustion Codes

    The Current Use of PDF/FDF‐Methods

    New Developments

    Common Activities to Develop a New Combustion Code

    Prospects for Further Developments

    The Current and Future Use of Computational Methods

    Some Challenges

    Design and Testing of Gasdynamically Optimized Fuel Injectors for the Piloting of Supersonic Flames with Low Losses

    Introduction

    Experimental Setup

    Model SCRamjet Combustor

    Preheater

    Combustion Chamber

    Injectors

    Investigation Tools

    Shadowgraph Method

    Rayleigh Scattering

    Raman Scattering

    OH‐LIF Measurements

    Self‐Fluorescence Measurements (Chemiluminescence)

    Numerical Modelling

    Numerical Simulation with the CFD‐Code Fluent 5.5

    Special Features of the Modelling of the Supersonic Combustion

    Reducing the Number of Species

    Reaction Mapping by Using of the Polynomials

    Validation of the Modelling Approach with Polynomials

    Two Stage Injector

    Theoretical Considerations

    Shock Stabilization

    Combustion

    Conclusions

    Hypersonic Propulsion Systems: Design, Dual‐Mode Combustion and Systems Off‐Design Simulation

    Combustion Stability of a Dual‐Mode Scramjet Configuration with Strut Injector

    Introduction

    Experimental Setup

    Results and Discussion

    Conclusions

    Hypersonic Highly Integrated Propulsion Systems Design and Off‐Design Simulation

    Introduction

    Reference Propulsion System for the TSTO Concept

    Engine Integration

    Core Engine

    Numerical Engine Simulation

    Thrust Vectoring

    Real Time Flight Simulation

    Conclusion

    Experimental Investigation about External Compression of Highly Integrated Airbreathing Propulsion Systems

    Introduction

    Focus on the Problem

    Preliminary Measurements

    Experimental Facility

    Wind Tunnel Models and Instrumentation

    Model 1

    Model 2

    Model 3

    Numerical Model

    Measurements and Results

    Determination of the Boundary‐Conditions

    Measurements in the Field of Shock Boundary Layer Interaction

    Conclusion and Outlook

    Experimental and Numerical Investigation of Lobed Strut Injectors for Supersonic Combustion

    Introduction

    Experimental Setup and Measurement Techniques

    Governing Equations and Numerical Simulation

    Multigrid Convergence Acceleration

    Strut Design and Performance Parameters

    Supersonic Mixing

    Supersonic Combustion

    Investigation of Different Lobed Strut Injectors

    Conclusions

    Experimental Studies of Viscous Interaction Effects in Hypersonic Inlets and Nozzle Flow Fields

    Introduction

    Experimental Techniques

    Facility and Flow Diagnostics

    Wind Tunnel Models

    Inlet Studies

    Nozzle Studies

    Conclusion

    Intake Flows in Airbreathing Engines for Supersonic and Hypersonic Transport

    Introduction

    Physical Model

    Numerical Method

    Results

    Turbulent 2D Supersonic Intake Flows with Internal Compression

    Laminar 3D Hypersonic Corner Flows

    Turbulent 3D Hypersonic Flows through Symmetric/Asymmetric Double‐Fin Configurations

    Laminar 2D Shock Interactions in Hypersonic Flows with Chemical Non‐Equilibrium

    Conclusions


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite




    Propulsion - Propulsion round-up

    Online Contents | 2000


    PROPULSION DEVICE, PROPULSION CONTROL DEVICE, AND PROPULSION CONTROL PROGRAM

    TAKEMURA YUICHI / HASHIMOTO MARIKO / KAWAZU SHINSUKE et al. | European Patent Office | 2024

    Free access