The Flyin' Lion is an electric light sport aircraft designed by a team of aerospace engineering students. It has a maximum takeoff weight of 1,300 lbs, a 46 ft wingspan, and is powered by an 80 hp electric motor. Flight endurance is estimated at 2.5 hours with a range of 220 miles at sea level cruise speed. The aircraft is designed to be environmentally friendly, cost effective to operate, and suitable as a trainer aircraft.

1. MIDTERM PRESENTATION
AEROSPACE 402B
The Flyin’ Lion
ELECTRIC LIGHT SPORT AIRCRAFT
ALEX KARNS
HARSHAD KAPOOR
STEVE BARR
DAVID BAVER
MIKE DISORI
CHRIS GUMKE
1

2. 3-VIEW
2

3. FRONT VIEW
2°
4.5 ft.
3

4. TOP VIEW
46 ft.
7 ft.
3.5 ft. 3 ft.
10 ft.
1 ft.
2 ft.
8 ft.
4

5. SIDE VIEW
13.3 ft.
3 ft.
4 ft.
6.25 2.5 ft.
ft. 2 ft. 6.5 ft.
CG. Location .35c and Neutral Point location at .44c
5

6. STABILITY AND CONTROL
• FWD CG LIMIT: -0.17c
– Based on CLmax in Ground Effect
• AFT CG LIMIT: 0.44c
– Based on Neutral Point Location
• MAX STATIC MARGIN: 9%
6

7. SIDE VIEW
7

8. STABILITY AND CONTROL
Component Weight of Part (lb.) CG location from nose (ft.)
Passengers 400 8.2
Batteries 400 3.5
Motor 42 12
Controller 30 2
Propeller 15 10
Seats 40 0.5
Tail 60 8.2
Fuselage +
313 7.5
Wing
Forward limit CG location Aft limit Static Margin
6.40 8.21 8.61 9% 8

9. SPECIFICATIONS
Parameters Value Parameters Value
Weight (lbs) 1300 Power Available (hp) 80.0
Span (ft) 46.0
Engine Efficiency 0.90
Root Chord (ft) 3.50
Max Propeller Efficiency 0.87
Tip Chord (ft) 3.00
Cabin Width (ft) 5.00
Wing Area (ft^2) 156
Wing Loading Vertical Tail Height (ft) 4.50
8.30
(lb/ft^2)
Base Vertical Tail Chord (ft) 4.00
Aspect Ratio 13.6
Taper Length (ft) 10.0 Tail Chord (ft) 2.00
Taper Ratio 0.94 Tail Span (ft) 8.00
Span Efficiency 0.96 Span Efficiency of Tail 0.95
9

10. AILERON SIZING
y2
y1
Aileron Size
y2 22 ft
y1 12 ft
Roll Rate 45 deg/sec 10

11. VERTICAL TAIL
Vertical Tail Sizing
Estimated Side Wash
0.17
Parameter *
Effective Tail Parameter 0.7
Vertical Tail Lift Slope 6.25/rad
Vertical Tail Volume 0.026
Weathercock Stability -0.04
Rudder Power -0.051
Rudder Deflection
9.12°
@ Max Sideslip **
* Ideal Side Wash Parameter from Morelli Paper
** IAW FAR Section 23 – Max sideslip for crosswinds is 11.5° 11

12. TURN PERFORMANCE
(BASED ON AERODYNAMIC PARAMETERS)
FAR Allowable Range: -1.5G to 3.8G
12

13. CABIN DRAWING
13

14. POWERPLANT AND BATTERIES
ENGINE:
YUNEEC POWER DRIVE 60 BATTERY ENERGY DENSITY:
240 WHr/Kg
POWER:
81 HP
BATTERY WEIGHT:
OPTIMUM RPM: 400 LBS
2,400
BATTERY EFFICIENCY:
WEIGHT: 0.90
66 LBS
14

15. WING AIRFOIL
NLF 0115
15

16. HORIZONTAL & VERTICAL TAIL AIRFOIL
EPPLER 521
16

17. TOTAL DRAG BUILD-UP
Airspeed Landing Gear Fuselage Wing Drag Empennage Total Drag
(kts) (lbs) Drag (lbs) (lb) Drag (lbs) (lbs)
40 0.64 4.20 53.17 0.29 58.30
43 0.74 4.78 47.11 0.32 52.96
45 0.81 5.19 43.80 0.34 50.15
50 1.00 6.28 37.44 0.40 45.11
75 2.25 13.03 26.19 0.76 42.23
100 4.00 21.86 28.45 1.24 55.55
120 5.76 30.35 34.33 1.72 72.15
140 7.84 40.05 42.57 2.29 92.75
17

18. TOTAL DRAG BUILD-UP
Total
Induced
Profile
18

19. LIFT TO DRAG RATIO
MAX L/D = 32
@ 65 KNOTS
19

20. POWER REQUIRED AND
AVAILABLE VS. VELOCITY
ft
ft
20

21. RATE OF CLIMB AND TIME TO CLIMB
(INCLUDING SERVICE AND ABSOLUTE CEILINGS)
NOTE: Because the Flyin’ Lion cannot carry oxygen, the highest altitude it can fly
is at 12,000 ft. The cruise altitude can be reached in approximately 4.3 minutes
assuming constant rate-of-climb and flying at maximum rate-of-climb velocity. 21

22. STALL SPEED
22

23. LIFT CURVE
23

24. ENDURANCE AND RANGE
• C = BATTERY ENERGY DENSITY
E = 2.5 HOURS & R = 220 MILES
@ SEA LEVEL, CRUISE SPEED • WB = BATTERY WEIGHT
• ηB = BATTERY EFFICIENCY
E = 3.5 HOURS & R = 360 MILES • ηC = CONTROLLER EFFICIENCY
@ SEA LEVEL, CRUISE SPEED WITH • ηB = PROPELLER EFFICIENCY
EXTENDED BATTERY PACK
• Preq = POWER REQUIRED
• V = VELOCITY
24

25. TAKE-OFF AND LANDING DISTANCES
GROUND ROLL:
SGROUND ROLL = 315.61 FT
LANDING DISTANCE:
SLANDING = 1341.85 FT
25

26. V-n Diagram
26

27. WEIGHT AND COST ESTIMATION
Engine, Motor, and Battery System
Component Weight (lbs) Cost ($) # of Parts Total Weight(lb) Total Cost ($)
Propeller 15 2500 1 15 2500
Electric Engine (80HP) 42 8200 1 42 8200
Battery Pack (Li Ion) 191 900 2 382 1800
Power Block 40
15.5 1789 1 15.5 1789
Controller
E Charger 15.4 900 1 15.4 900
Electric Wiring System 1.9 400 4 7.6 1600
Engine Cowling 20 1300 1 20 1300
Spinner Cover 1 340 1 1 340
Section Total: 498.5 18429
27

28. WEIGHT AND COST ESTIMATION
Cockpit Fuselage, Instruments and Controls
Total Cost
Component Weight (lbs) Cost ($) # of Parts Total Weight (lbs)
($)
Aircraft Seats 20 100 2 40 200
Instrument Panel 19.5 6138 1 19.5 6138
Flight Controls 2 140 2 4 280
Canopy 10 1469 1 10 1469
Restrain Belts 4 80 2 8 160
Rudder Pedals 2 229 2 4 458
Flight Control Linkages 25 1900 1 25 1900
Composite Skin/ Fuselage 45 2800 1 45 2800
Passengers 200 0 2 400 0
Section Total: 555.5 13405
28

29. WEIGHT AND COST ESTIMATION
Wing, Ailerons, and Structure
Total Total Cost
Component Weight (lbs) Cost ($) # of Parts
Weight (lbs) ($)
Composite Wing, Aileron,
146 9100 1 146 9100
and Skin Structures
Aifrcraft Lights 0.5 120 4 2 480
Section Totals: 148 9580
Empennage and Tail Boom
Weight Cost # of Total Weight Total Cost
Component
(lbs) ($) Parts (lbs) ($)
Composite Tail Boom,
Horizontal and Vertical Tail, and 60 3800 1 60 3800
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Skin/ Structure

30. WEIGHT AND COST ESTIMATION
Forward and Main Landing Gear, Tires, and Wheel Pants
Weight Cost # of Total Weight Total Cost
Component
(lbs) ($) Parts (lbs) ($)
Landing Gear Struts 3 140 3 9 420
Tires 4 114.95 3 12 344.85
Wheel Pant Composite Skin 1 70 3 3 210
Section Totals: 24 974.85
Overall System Totals:
Cost ($) 46k
Weight (lbs) 1286
30

31. KEY POINTS
• Environmentally Friendly
• Cost Effective
– Low Operating Costs
– Low Unit Cost
• iPad integrated
• Quiet
• Trainer Aircraft
– Easy Learning Curve
• Excellent Maneuverability

32. KEY POINTS
• Modern Instrument Panel
• LSA Certifiable
• Lightweight Composite Design
• Laminar Flow Airfoil
– Low Drag
• FUN

33. QUESTIONS
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