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Propulsion PDR #2 AAE451 – Team 3 November 11, 2003

Propulsion PDR #2 AAE451 – Team 3 November 11, 2003. Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian. Aircraft Walk Around. Wing Span = 14 ft A/C Length = 10 ft. Conventional Tail – NACA 0012. Pusher. Internal Pod. Low wing – Clark Y. Tricycle Gear.

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Propulsion PDR #2 AAE451 – Team 3 November 11, 2003

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  1. Propulsion PDR #2 AAE451 – Team 3 November 11, 2003 Brian Chesko Brian Hronchek Ted Light Doug Mousseau Brent Robbins Emil Tchilian

  2. Aircraft Walk Around • Wing Span = 14 ft • A/C Length = 10 ft • Conventional Tail – NACA 0012 • Pusher Internal Pod • Low wing – Clark Y • Tricycle Gear

  3. Method for Propulsion Selection • Use constraint diagram and takeoff EOM to determine required engine size • Use modified gold.m in a loop to make plots • Pick prop pitch and diameter from gold.m results • Show brief analysis of fuel consumption

  4. Constraint Diagram

  5. Takeoff EOM Integration Drag + Rolling Friction Thrust T = Thrust D = Drag m = Rolling Friction Factor (0.05 for dry concrete) • Assumptions • No lift to reduce effects of friction • Max thrust occurs instantaneously

  6. Static vs. Forward Flight Thrust Static Thrust Forward Flight Thrust Raymer (13.17) n = rotation speed (rev/s) D = Propeller diameter (ft) V = Velocity (ft/s) • Using Forward Flight Thrust leads to very large velocities at low velocities. How large?

  7. Forward Flight Thrust vs. Time Forward Flight Thrust reaches ~ 12,000 lbf at time = 0

  8. Static Thrust Used for Integration • cT, cP found for each step of integration using gold.m • gold.m updated for results from most current prop analysis (shown later in the presentation)

  9. Takeoff Distance based on ODE

  10. Chosen Engine • O.S. Max 1.60 FX-FI • $714.99 w/o muffler • 3.7 BHP @ 8500 RPM • 1,800-9,000 RPM • 2.08 lbs • Benefits of Fuel Injection • Vs non FI • Easier starting • More stable idling • Excellent throttle response • Pressurized fuel supply does not depend on engine orientation • Electronic control of engine parameters Ref. www.towerhobbies.com Ref. O.S. 1.60FX-FI Owners Manual

  11. Thrust vs. Horsepower RPM = 8500

  12. Thrust vs. Horsepower RPM = 8500

  13. RPM vs. Efficiency Cruise T = 4.0 lbf Stall T = 5.6 lbf

  14. RPM vs. Efficiency Cruise T = 4.0 lbf Stall T = 5.6 lbf

  15. RPM vs. Power Required Stall T = 5.6 lbf Cruise T = 4.0 lbf

  16. RPM vs. Power Required Stall T = 5.6 lbf Cruise T = 4.0 lbf

  17. Chosen Propeller – 2 blades • Based on carpet plots from gold.m: • RPM used (cruise) = 5350 (~63% of 8500 max HP rpm) • Pitch is 6 inches • Diameter is 20 inches • Efficiency at cruise ~ 0.66 • Efficiency at stall ~ 0.47

  18. Chosen Propeller 4-blades • Zinger 18X5 Wood Pusher Propeller • 18 inches in diameter with 5 inch pitch • 4 blades • Conversion from 2-bladed to 4-bladed based on Zinger recommendations: • For 2 blade to 3 blade: lower diameter only • For 2 blade to 4 blade: lower diameter and pitch • Therefore, we chose a 18X5 four blade instead of a 20X6 two blade Ref. www.zingerpropeller.com

  19. Fuel Consumption • Fuel Consumption based on data from O.S. Engines • O.S. Max 1.60 FX-FI uses approx. 500 mL for 11 minute flight (~1364 mL for 30 min.) • 1364 mL ~ 0.36 gal ~ 2.2 lbf ~ 46 oz. • This number is based on guidelines given by O.S…..our number could be slightly different Ref. www.towerhobbies.com

  20. Chosen Fuel Tank • Fuel tank chosen is: • Du-Bro 50 oz. fuel tank • $11.49 from Tower Hobbies • Located at the C.G. of aircraft Ref. www.towerhobbies.com

  21. Future Actions • Continue working with EOM analysis • Look for accurate HP versus RPM curves • Continue with 4-bladed propeller code • Search for engine closer matching the requirements

  22. Questions?

  23. Appendix

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