Combustion of solid fuels in a high-temperature supersonic airstream

Autor:	L. J. Spadaccini, W. Chinitz
Rok vydání:	1969
Předmět:	Propellant Hypersonic speed Stagnation temperature Materials science business.product_category Rocket Nuclear engineering Aerospace Engineering Combustion Stagnation pressure Solid fuel business Adiabatic flame temperature
Zdroj:	AIAA Journal. 7:1682-1687
ISSN:	1533-385X 0001-1452
Popis:	The basic purpose of this investigation was the study of ablation and combustion processes applicable to solid propellants which are potentially suitable for use in hybrid or air-augmented rocket systems, in pure air-breathing engine systems, and external burning schemes. The results of an experimental program conducted employing cones and hemisphere-cylinder shapes fabricated of Plexiglas and nylon are presented. The plastic models were tested in a Mach number 2.0 wind tunnel at stagnation temperatures between 1400° R and 3400° R, and at a stagnation pressure of 118 psia. The feasibility of burning the ablation products of these materials in a high-temperature hypersonic airstream has been demonstrated, and the parameters that affect the ablation and combustion processes are discussed. In addition, the ablating mass flow rate has been compared with predictions obtained from a semi-empirical analysis of heat transfer and subliming ablation. The agreement obtained is sufficiently accurate to permit the use of the analysis for engineering design estimates.
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=doi_________::731c201e42b78c22a0aa67435d461c09 https://doi.org/10.2514/3.5375 Zobrazit plný text záznamu