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Uploaded by ajmarchese on Apr 18, 2009
Successful hybrid rocket motor test firing. December 16, 2005. Fuel: 80% HTPB/20% Al Oxidizer: GOX. Ae/At: 3.6 L: 12 in. dp: 0.5 in. Thrust: 6.5 lbf Pc: 150 psi
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