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AME436-S08-PS7 - AME 436 Problem Set#7 Assigned"Due but no...

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AME 436 Assigned: 4/30/08 Problem Set #7 “Due” 5/2/08 but no late penalty until 5/6/08, 12:00 noon; no assignments accepted after that date – NO EXCEPTIONS! (Fax to me at 213-740-8071 if you’re off campus.) NOTE: since your lowest homework grade will be eliminated anyway, if you’re satisfied with your other grades you can skip this one. (Not recommended, however.) Problem #1 Draw each of the following hypersonic propulsion cycles on the attached T-s diagrams (starting in the lower left corner of the figure). Draw additional Rayleigh/Fanno lines as needed. a) Conventional ramjet with poor diffuser (non-isentropic) and maximum (constant-area) heat addition b) "Scramjet" with (isentropic) inlet diffuser, normal shock, and heat addition at increasing area c) "Scramjet" with no inlet diffuser, normal shock, maximum (constant-area) heat addition, partial (isentropic) expansion (i.e. not all the way to P e = P a , supersonic afterburner (!) with decreasing area, and finally isentropic expansion to P e = P a . a)
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b) c) Problem #2 A hypersonic aircraft is in level flight at M 1 = 10 at 100,000 ft altitude and uses H 2 fuel. The ambient air temperature is 227K and the ambient pressure is 0.0108 atm. The maximum pressure inside the engine is limited to 100 atm by structural considerations. Using GASEQ, determine the performance of this pressure-limited stoichiometric-burning H 2 -air engine in the following way: a. Choose as reactants “hydrogen-air flame” and as products “H2/O2/N2 products.” The default mixture strength is stoichiometric, so you shouldn’t have to change that. Choose 227K and 0.0108 atm as the reactant conditions. Then select Problem Type “Adiabatic compression/expansion” and check the “frozen composition” box. Choose a product pressure P 2 = 100 atm and hit the “Calculate” button. Note the enthalpy (h 1 ) and sound speed (c 1 ) of the reactants at ambient conditions, and calculate the flight velocity u 1 = c 1 M 1 .
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