5. Design a nozzle to pass a mass flow rate of 1000 lbm/s between a pressure chamber (Pc=3000 psia, and Tc= 3700 °R), an

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5 Design A Nozzle To Pass A Mass Flow Rate Of 1000 Lbm S Between A Pressure Chamber Pc 3000 Psia And Tc 3700 R An 1 (133.99 KiB) Viewed 46 times

5. Design a nozzle to pass a mass flow rate of 1000 lbm/s between a pressure chamber (Pc=3000 psia, and Tc= 3700 °R), and an exhaust region Pe with a variation in pressure between the two regions. a. Using the design conditions complete the attached table, b. Make a plot of the nozzle contour, to scale, no hand plots allowed, C. Calculate the nozzle design (optimum performance) performance ration Pn= Pc/Pa d. Calculate the nozzle design area ratio, e. Using the altitude table, determine the design altitude for this nozzle (Pe=Pa) f. Determine the thrust of a rocket motor using this nozzle at its design altitude. Station x (in) P(psia) T/Tt A/A* T(OR) a (ft/s) v (ft/s) A (in?) D (in) P/Pt 0.972 7 M 0.199 4 9921 2.9719 570.8 2969.8 592.2 3.31 12.01 2918 2841 2 4 olto 9 2687 2529 6 2124 8 10 throat 1585 0.8333 1 12 16 727 218 3.999 2 24 19.8 1122.2 41 60 3.21 1.17