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Aerospike Hybrid Rocket Motor 2006

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Uploaded by on Dec 1, 2007

UPDATE: 1ST PLACE UNDERGRADUATE 2008 AIAA REGION VI STUDENT CONFERENCE

Lab scale experiment of an aerospike nozzle and its compatibility with a hybrid propulsion system. This particular static test was just for a few seconds and about 146 lbs of thrust done in Spring of 2006 and used in an Independent Study for credit at the University of Washington.

James Stoffel

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Science & Technology

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Uploader Comments (doc34thumper)

  • AIAA uh, cool, I'll have to try looking it up...who knows, I may have already. Have you used a contoured nozzle instead of conical? What did you make the nozzle out of?

  • actually the paper is going through touch ups before resubmittal for the international conference, so actually i dont know when the paper will be up officially on the website. i havnt used a contour nozzle yet, due to literature only 1% performance is really lost for conical. we are also working on a 20% truncated nozzle with base bleed. this nozzle was made of mild steel, as for the new one, it is graphite for now for shorter burn times, due to dual throat erosion for long burns.

  • Pretty dang cool.

  • hey thanks! new research and results coming in the next two months.

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  • Nice, congrats. Is your paper up?

  • ah ok, I'll keep my eyes open for your paper. I'm not sure if I'll submit my report, depends on my final grade for it I guess.

  • that was awesome! sure made a mess of everything!!

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