assignment3 - Space Flight Dynamics and Propulsion Systems...

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1 Space Flight Dynamics and Propulsion Systems MECH 6251/498D Department of Mechanical and Industrial Engineering Concordia University Assignment #3 Nozzle theory and ideal rocket design Due: Tuesday, November 30, 2010 Instructions: Answer all questions; ensure your homework assignment is completed properly. Please clearly write down your name and student ID. List all necessary assumptions and the models you used. Show all calculations and units. Problem 1: The actual conditions for an optimum expansion nozzle operating at sea level are given below. Calculate v 2 , T 2 , and C F . The mass flow m = 3.7 kg/sec; p l = 2.1 MPa; T 1 = 2585 K; R s = 18.0 kg/kg-mol; and γ = 1.30. Problem 2: The following data are given for an optimum rocket: Average molecular mass 24 kg/kg-mol Chamber pressure 2.533 MPa External pressure 0.090 MPa Chamber temperature 2900 K Throat area 0.00050 m 2 Specific heat ratio 1.30 Determine (a) throat velocity; (b) specific volume at throat; (c) propellant flow and specific impulse; (d) thrust; (e) Mach number at throat. Determine the ideal thrust coefficient by two
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This note was uploaded on 12/12/2010 for the course MECH 351 taught by Professor Chekhov during the Fall '10 term at Concordia Canada.

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assignment3 - Space Flight Dynamics and Propulsion Systems...

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