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

AAE 451 Team 3 2 Aircraft Walk Around Low wing – Clark Y Tricycle Gear Conventional Tail – NACA 0012 Pusher Wing Span = 14 ft A/C Length = 10 ft Internal Pod

AAE 451 Team 3 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

AAE 451 Team 3 4 Constraint Diagram

AAE 451 Team 3 5 Takeoff EOM Integration T = Thrust D = Drag  Rolling Friction Factor (0.05 for dry concrete) Assumptions No lift to reduce effects of friction Max thrust occurs instantaneously Thrust Drag + Rolling Friction

AAE 451 Team 3 6 Static vs. Forward Flight Thrust Static Thrust Forward Flight Thrust n = rotation speed (rev/s) D = Propeller diameter (ft) V = Velocity (ft/s) Raymer (13.17) Using Forward Flight Thrust leads to very large velocities at low velocities. How large?

AAE 451 Team 3 7 Forward Flight Thrust vs. Time Forward Flight Thrust reaches ~ 12,000 lbf at time = 0

AAE 451 Team 3 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)

AAE 451 Team 3 9 Takeoff Distance based on ODE

AAE 451 Team 3 10 Chosen Engine O.S. Max 1.60 FX-FI –$ w/o muffler – RPM –1,800-9,000 RPM –2.08 lbs Ref. O.S. 1.60FX-FI Owners Manual 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.

AAE 451 Team 3 11 Thrust vs. Horsepower RPM = 8500

AAE 451 Team 3 12 Thrust vs. Horsepower RPM = 8500

AAE 451 Team 3 13 RPM vs. Efficiency Stall T = 5.6 lbf Cruise T = 4.0 lbf

AAE 451 Team 3 14 RPM vs. Efficiency Stall T = 5.6 lbf Cruise T = 4.0 lbf

AAE 451 Team 3 15 RPM vs. Power Required Stall T = 5.6 lbf Cruise T = 4.0 lbf

AAE 451 Team 3 16 RPM vs. Power Required Stall T = 5.6 lbf Cruise T = 4.0 lbf

AAE 451 Team 3 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

AAE 451 Team 3 18 Chosen Propeller 4-blades Zinger 18X5 Wood Pusher Propeller –18 inches in diameter with 5 inch pitch –4 blades Ref. 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

AAE 451 Team 3 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.

AAE 451 Team 3 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.

AAE 451 Team 3 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

AAE 451 Team 3 22 Questions?

AAE 451 Team 3 23 Appendix