PROPULSION QDR 1 AAE 451 TEAM 4 Jared Hutter, Andrew Faust, Matt Bagg, Tony Bradford, Arun Padmanabhan, Gerald Lo, Kelvin Seah October 28, 2003

OVERVIEW Roadmap to Engine and Propeller Selection Engine Selection Propeller Analysis & Choice Follow-Up Actions

CONSTRAINT DIAGRAM single engine operation Propeller Efficiency of 54% used

ROADMAP TO ENGINE SELECTION Calculations based on single-engine flight From the Constraint Analysis, Power Loading, W/P = 38 lbf / SHP From Preliminary Weight Estimate, Gross Take-Off Weight, WTO = 54.52 lbf Total Required Power = 1.4 HP

ENGINE CHOICE Engine Choice: Saito FA-100 Specifications: Bore: 29.0 mm Stroke: 26.0 mm Displacement: 1.0 cu. in. Practical RPM: 2,100 - 9,700 Power: 1.8 BHP @ 9500 RPM Weight: 20.8 oz Source: http://horizon.hobbyshopnow.com/products/description.asp?prod=SAIE100&ptab=tech

DRAG ANALYSIS & REQUIRED THRUST Span efficiency, e 0.6 Aspect Ratio, AR 5 Lift Coefficient, CL 1.03 Induced Drag Coefficient, CDi 0.112 Parasitic Drag Coefficient, CD0 0.06 Drag Coefficient, CD = CD0 + CDi 0.172 Wing Area, S 47.08 ft2 Velocity = Vstall * 1.2 = 28 ft/s * 1.2 = 33.6 ft/s Density, ρ = 0.002377 slug/ft3 Drag = 10.4 lbf

DRAG ANALYSIS & REQUIRED THRUST (continued) Drag = 10.4 lbf Pitch Angle,  = 0.5 Weight = 54.52 lbf Thrust = Drag + Weight*sin() = 10.9 lbf L T V D  W 

ROADMAP TO PROPELLER SELECTION Varied propeller diameter and pitch to match engine  propeller  airframe Matched manufacturer’s HP @ optimum RPM Matched thrust and velocity requirements from constraint analysis and mission requirements.

PROPELLER ANALYSIS Gold.m was used to produce all results Key in Inputs The desired blade diameter and pitch Manufacturer specified optimum RPM (9500 rev/min) Desired operating flight velocity (33.6 ft/s) Re-iterate using Outputs Horsepower and Thrust Final desired Outputs 1.8 HP @ 9500 RPM  10.9 lbf of thrust

PROPELLER ANALYSIS 9500 RPM 6”

PROPELLER ANALYSIS 9500 RPM 6”

PROPELLER CHOICE Diameter: 16” Pitch: 6” RPM: 9,500 rev/min Power: 1.8 HP Advance Ratio: 0.159 rev-1 Power Coefficient: 0.0248 Thrust Coefficient: 0.0568 Efficiency: 36.4% 16” x 6” $37

CONSTRAINT DIAGRAM single engine operation Propeller Efficiency of 36.4% used  2.47HP engine required Underpowered  Iterate with new engine and propeller

FOLLOW-UP ACTIONS Continue analysis to finalize engine and propeller Study twin engine performance

QUESTIONS?