PROPULSION QDR 2 AAE 451 TEAM 4 Jared Hutter, Andrew Faust, Matt Bagg, Tony Bradford, Arun Padmanabhan, Gerald Lo, Kelvin Seah November 20, 2003

CONCEPT REVIEW Empennage High Wing Twin Booms Twin Engine Avionics Pod S = 34.5 ft2 b = 13.1 ft, c = 2.6 ft AR = 5 Twin Booms 3 ft apart; 7.3 ft from Wing MAC to HT MAC Twin Engine 1.8 HP each Avionics Pod 20 lb; can be positioned front or aft depending on requirements Empennage Horizontal and Vertical Tails sized using modified Class 1 Approach (per D & C QDR 1)

OVERVIEW Overview of Engine Used Thrust Analysis Propeller Selection, Analysis & Choice Summary of Results Follow-Up Actions

ENGINE CHOICE Engine Choice: Saito FA-100 Specifications: Weight: 20.8 oz Bore: 29.0 mm Stroke: 26.0 mm Displacement: 1.0 cu. in. Practical RPM: 2,100 - 9,300 Power: 1.8 BHP @ ~9100 RPM Fuel Consumption Rate: 1 oz/min $279.99 at maximum RPM Source: http://www.saitoengines.com

DRAG ANALYSIS & REQUIRED THRUST performed for OEI condition Span efficiency, e 0.6 Aspect Ratio, AR 5 Lift Coefficient, CL 0.98 Induced Drag Coefficient, CDi 0.102 Parasitic Drag Coefficient, CD0 0.06 Drag Coefficient, CD = CD0 + CDi 0.162 Wing Area, S 34.46 ft2 Velocity = 1.2 Vstall = 1.2 28 ft/sec = 33.6 ft/sec Density, ρ = 0.002377 slug/ft3 Drag = 7.5 lbf

DRAG ANALYSIS & REQUIRED THRUST (continued) Drag = 7.5 lbf Flight Path Angle,  = 0.5 Weight = 54.5 lbf Thrust = Drag + Weight*sin() = 8 lbf L T V D  W 

PROPELLER ANALYSIS PROCEDURE Ensured that Gold.m was accurate. Modified Gold.m to incorporate actual propeller chord distributions for specific propellers. Plotted results to finalize propeller choice. Twin engine performance characteristics.

BELIEVABILITY CHECK First Place Engine, FPE 1.3ci Specifications 16x8 RECOMMENDED PROP 2,000 to 7,400 rpm RPM RANGE 10 lbs @7,400 rpm THRUST 43.2 ounces (including muffler) WEIGHT 1.3 cubic inches (21cc) DISPLACEMENT First Place Engine, FPE 1.3ci http://www.fpengines.com Gold.m results using a 16” x 8” propeller: Model Propeller Geometry: Tstatic = 9.9 lbs @ 7400RPM Zinger Propeller Geometry: Tstatic = 11.9 lbs @ 7400RPM Propeller Geometry Source: http://www.ace.gatech.edu/experiments2/6514/aircraft/fall02/propeller.htm

TWIST DISTRIBUTION

PROPELLER ANALYSIS

PROPELLER ANALYSIS lbf

PROPELLER ANALYSIS

ENGINE PARAMETERS Single Engine Flight (V = 33.6 ft/s) CP = 0.0274 CT = 0.0619 J = 0.1662 HP = 1.74 @ 9100 RPM  = 37.5% T = 10.7 lbf Twin Engine Flight (V = 60 ft/s) CP = 0.0185 CT = 0.0337 J = 0.1662 HP = 0.54 @ 7000 RPM  = 70% T = 3.44 lbf/engine = 6.88 lbf

FOLLOW-UP ACTIONS Contact engine manufacturer for further engine details Finalize fuel feed system

QUESTIONS?