Thermofluiddynamics of Optimized Rocket Propulsions

- Synopsis
- One (I): Optimal Comparative Process for Rocket Engines
1. Description of the Problem
1.1 Introduction
1.2 NASA Comparative Processes
2. Definition of an Ideal Comparative Process
2.1 Process Phenomenology in a Rocket Engine
2.2 Comparative Process for Relaxing Flows
3. Classical Gas Dynamics of the ICP
3.1 Relaxing Model Gas as System
3.2 Flow Tube Theory with Conversion Processes
3.3 Sequence of States
4. Design Criteria for Rocket Engines
4.1 Design Procedure
4.2 Influences of Real Flows
5. Summary I
- Two (II): Thermofluiddynamics of Rocket Propulsion
1. Problems with the NASA-Methods
1.1 Intentions of the NASA-Lewis Code
1.2 AFC Method
1.3 FAC Method and Prozan's Procedure
1.4 Evaluation of the NASA Methods
1.5 Matching Procedures
1.6 General Commentary
2. Basic Principles of the Alternative Theory
2.1 Introduction and Reference to the Microphysical Fundamentals
2.2 Forms of Energy and Gibbs Fundamental Equation
2.3 Gibbs-Duhem Equation, Process and Realization
2.4 Axioms of the Traditional Continuum Theories: a Commentary
2.5 Significant Results of the Alternative Theory: an Outline
3. The Munich Method
3.1 Preliminary Remarks
3.2 Changes of State in the Combustion Chamber
3.3 Speed of Sound in Chemically-reacting Gas Mixtures
3.4 Stoichiometric Matrix of the LH-LOX Equilibrium Combustion
3.5 Nozzle Differential Equation; Mass Flow Eigenvalue
3.6 Nozzle Exit State: Problems of Numerical Computation
3.7 Regenerative Cooling: Attempts towards a Modeling
4. Test of the MM with Data from LH-LOX Rocket Engines
4.1 Problems of Assessment
4.2 MM in Comparison with the Lewis Code and Test Data
4.3 Variable Mixture Ratios and Reusability
4.4 Influence of the Operating Parameters on Flow States
5. Summary Part II
- List of Relevant Symbols
- Appendix 1: Thermodynamic Analysis of the Simplified Model Gas
- Appendix 2: Properties of State of Polynary Fluid Mixtures
- Notes
- Index of Names