Latest News - 6/1/08

I've been working on the design for the next engine the past few months. It will be a 200-250 lbf regen engine with LOX/Kerosene as the propellants, essentially the same design as the 100 lbf engine I've been testing but with some changes (O-rings for seals instead of Grafoil, etc.). One of the parameters I wanted to determine from the 100 lbf regen tests was the gas side heat transfer coefficient so I could use it to correct my design equations. I've done that and used an hg correction value (x1.45) for the design of the new one but I'm wondering whether I'm using the proper methodology to determine it. I'll go over the method I used when I get a chance to write it up.

Since I plan to use this new engine to fly in a rocket, I'm trying to decide on the exact thrust level I need. I don't have a lot of empirical data yet for empty weights of the various parts in a vehicle but I suspect the empty weight will be heavier than I expect. The vehicle will be designed for a 30-40 second burn time so I'm hoping the new amateur rocketry regulations get approved in the next year or so which lift the 15-second burn time limit.

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