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I believe that's the mass ratio. The liquid rocket propellants page on Wikipedia gives 2.77:1 as the mass ratio; the optimum varies with the exact engine design.
There's some interesting discussion of fuel ratios in this old usenet article.
I believe that's the mass ratio. The liquid rocket propellants page on Wikipedia gives 2.77:1 as the mass ratio; the optimum varies with the exact engine design.
I believe that's the mass ratio. The liquid rocket propellants page on Wikipedia gives 2.77:1 as the mass ratio; the optimum varies with the exact engine design.
There's some interesting discussion of fuel ratios in this old usenet article.
I believe that's the mass ratio. The liquid rocket propellants page on Wikipedia gives 2.77:1 as the mass ratio; the optimum varies with the exact engine design.
