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Problem 1: Rocket Trajectory

Problem 1: Rocket Trajectory. Write a computer code to predict flight of the V-2 rocket. Rocket info: http://en.wikipedia.org/wiki/V-2_rocket Drag (and lift) profile, next slide Constant thrust, constant exhaust speed Comment on all results Assumptions 1 DOF vertical (no lift)

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Problem 1: Rocket Trajectory

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  1. Problem 1: Rocket Trajectory • Write a computer code to predict flight of the V-2 rocket. • Rocket info: http://en.wikipedia.org/wiki/V-2_rocket • Drag (and lift) profile, next slide • Constant thrust, constant exhaust speed • Comment on all results • Assumptions • 1 DOF vertical (no lift) • Constant gravity (then make gravity a function of altitude) • Use the standard atmosphere under standard day conditions • List all other assumptions you make (CG, CP, Iij, etc.) • Extra credit • Add a thrust profile (throttle) and variable exit velocity • 2 DOF flight (launch angles of 90, 80, 70 and 45 degrees) • Zero angle of attack (zero lift) • Then include angle of attack as calculated as the angle between the rocket centerline (long axis) and the velocity vector • Add a wind profile • Multi-DOF simulation (gets complicated!) • Integrate your code with predictions from NASA CEA (we will see this in 2 weeks)

  2. Variation of lift and drag coefficient with Mach number of V-2 rocket missile based on body cross-sectional area with jet off

  3. Brayton Cycle • Identify a modern commercial or military jet engine (turbofan or turbojet) • Plot the Brayton cycle • P-v diagram • T-s (or h-s) diagram • Identify relevant parameters • Comment on all results • Assumptions • Isentropic compression and expansion • Constant gas properties and specific heats • Non-constant gas properties (look these up in NIST or calculate on your own) • Mix of air and kerosene (or any other jet fuel you like, such as JET-A or even RP-1) • Show cycle for compressor and turbine efficiencies of 100, 90 and 80%

  4. BRAYTON CYCLE FOR SIMPLE GAS TURBINE Pressure ratio 40, inlet temperature =288K, turbine temperature 1700K, turbine and compressor adiabatic efficiencies both 0.9 [Cumpsty]

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