Experimental Investigation of Mist Injection at the Stagnation Point of a Blunt Body in Hypersonic Flow
A spacecraft re-entering Earth’s atmosphere at orbital speeds or higher is subjected to severe aerodynamic heating. Generally, large angle sphere-cone configurations are preferred as forebody to minimize aerodynamic heating. Though these configurations reduce heat transfer to some extent, they are not alone sufficient to withstand the harsh conditions existing during re-entry.
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