Thermal protection system (TPS) typically use materials which ablate at high temperature for mass-efficient rejection of aerothermal heat load. A reliable numerical procedure that can compute surface recession rate, mass loss, surface heat flux, and surface temperature distribution under general heating conditions is essential to successfully carry out the design of an optimum TPS. Thus, in order to improve estimating of the heat flux over an ablating surface, a flow solver coupled with ablating surface conditions becomes a requirement. A study have been conducted to predict nozzle recession behaviour in a solid rocket motor nozzle and for broad variations of motor operating conditions.

CFD Boundary Conditions for the Interaction of Rocket Nozzle Flows with Ablating Walls / Bianchi, Daniele; E., Martelli; Nasuti, Francesco. - ELETTRONICO. - (2008), pp. 1-10. ((Intervento presentato al convegno 2nd International Symposium on Propulsion for Space Transportation tenutosi a Heraklion, Creta, Grecia nel 5-8 maggio 2008.

CFD Boundary Conditions for the Interaction of Rocket Nozzle Flows with Ablating Walls

BIANCHI, DANIELE;NASUTI, Francesco
2008

Abstract

Thermal protection system (TPS) typically use materials which ablate at high temperature for mass-efficient rejection of aerothermal heat load. A reliable numerical procedure that can compute surface recession rate, mass loss, surface heat flux, and surface temperature distribution under general heating conditions is essential to successfully carry out the design of an optimum TPS. Thus, in order to improve estimating of the heat flux over an ablating surface, a flow solver coupled with ablating surface conditions becomes a requirement. A study have been conducted to predict nozzle recession behaviour in a solid rocket motor nozzle and for broad variations of motor operating conditions.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/358457
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