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

2. 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)

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

4. 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, ,300
Power: 1.8 ~9100 RPM
Fuel Consumption Rate: 1 oz/min
$279.99
at maximum RPM
Source:

5. 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
Parasitic Drag Coefficient, CD
Drag Coefficient, CD = CD0 + CDi
Wing Area, S ft2
Velocity = 1.2 Vstall = 1.2 28 ft/sec = 33.6 ft/sec
Density, ρ = slug/ft3
Drag = 7.5 lbf

6. 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 

7. 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.

8. BELIEVABILITY CHECK First Place Engine, FPE 1.3ci
Specifications
16x8
RECOMMENDED PROP
2,000 to 7,400 rpm
RPM RANGE
10 rpm
THRUST
43.2 ounces (including muffler)
WEIGHT
1.3 cubic inches (21cc)
DISPLACEMENT
First Place Engine, FPE 1.3ci
Gold.m results using a 16” x 8” propeller:
Model Propeller Geometry: Tstatic = RPM
Zinger Propeller Geometry: Tstatic = RPM
Propeller Geometry Source:

9. TWIST DISTRIBUTION

10. PROPELLER ANALYSIS

11. PROPELLER ANALYSIS
lbf

12. PROPELLER ANALYSIS

13. ENGINE PARAMETERS Single Engine Flight (V = 33.6 ft/s) CP = 0.0274
CT =
J =
HP = 9100 RPM
 = 37.5%
T = 10.7 lbf
Twin Engine Flight
(V = 60 ft/s)
CP =
CT =
J =
HP = 7000 RPM
 = 70%
T = 3.44 lbf/engine = 6.88 lbf

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

15. QUESTIONS?