Abstract
Part II of this study is divided into two main sections. The first presents a comparison and critical commentary on current organisation- and calculation-procedures for equilibrium combustion in high-performance rocket propulsions, based on flow tube theory. The basic defects of today’s virtually standard NASA-Lewis Code by S.Gordon & B.J.McBride are individually presented and analyzed. A comprehensive evaluation of the Code is given in Section 1.6.
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© 1989 Brikhäuser Verlag, Basel
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Straub, D. (1989). Summary Part II. In: Thermofluiddynamics of Optimized Rocket Propulsions. Birkhäuser Basel. https://doi.org/10.1007/978-3-0348-9150-9_11
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DOI: https://doi.org/10.1007/978-3-0348-9150-9_11
Publisher Name: Birkhäuser Basel
Print ISBN: 978-3-0348-9927-7
Online ISBN: 978-3-0348-9150-9
eBook Packages: Springer Book Archive