Abstract
In this book, we employ approximate relations for the determination of aerothermodynamic data. These are used in order to give quantitative information and to illustrate phenomena. In order to be sufficiently self-consistent, we provide these relations as well as others here. Derived are first elements of the RHPM+ flyer and the γeff approach together with the bow shock total pressure loss. Some γeff results in the large Mach number limit are given. Then the used or referred-to relations for the estimation of transport properties are provided, and finally formulas for stagnation point heating and flat surface boundary layer parameters.References are provided in all instances. For more general and detailed information the reader is referred to [1].
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Hirschel, E.H., Weiland, C. (2009). The γeff Approach and Approximate Relations for the Determination of Aerothermodynamic Parameters. In: Selected Aerothermodynamic Design Problems of Hypersonic Flight Vehicles. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-89974-7_10
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DOI: https://doi.org/10.1007/978-3-540-89974-7_10
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