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The burning rates of two fuel propellants, types A and B, are studied. It is assumed that the burning rates for the two prope

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Glve DA= 36 XAIN N MA = 5.3 66 1.082 | XBin NMB = 4.2, 609.801 ther TAN N do 25.a. 6 A 350 Dono HUB= ha 982 PR FA-RB A- us he

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