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_rockethttp://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, I ij, 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) 1

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

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% 3

4. 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]