Radiative Heat Transfer in Solid Rocket Nozzles

The radiative heat transfer within solid propellant rocket motor nozzles due to the emission and isotropic scattering by the liquid-phase alumina particles present in the combustion products is investigated. A method is presented for computing the effective absorption and scattering coefficients. Th...

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Veröffentlicht in:	Journal of spacecraft and rockets 2020-03, Vol.57 (2), p.247-260
1. Verfasser:	Cross, Peter G
Format:	Artikel
Sprache:	eng
Schlagworte:	Aluminum oxide Boundary conditions Boundary layers Combustion products Heat flux Liquid phases Nozzle walls Nozzles Particle size distribution Propellant transfer Radiative heat transfer Refractivity Rocket engines Rocket nozzles Scattering coefficient Solid propellants
Online-Zugang:	Volltext
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