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

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

3. CONSTRAINT DIAGRAM single engine operation
Propeller Efficiency of 54% used

4. 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 = lbf
Total Required Power = 1.4 HP

5. ENGINE CHOICE Engine Choice: Saito FA-100 Specifications:
Bore: 29.0 mm
Stroke: 26.0 mm
Displacement: 1.0 cu. in.
Practical RPM: 2, ,700
Power: RPM
Weight: 20.8 oz
Source:

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

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

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

9. 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
RPM  10.9 lbf of thrust

10. PROPELLER ANALYSIS
9500 RPM 6”

11. PROPELLER ANALYSIS
9500 RPM 6”

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

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

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

15. QUESTIONS?