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MIDTERM PRESENTATIONAEROSPACE 402B

The Flyin’ LionELECTRIC LIGHT SPORT AIRCRAFT

ALEX KARNSHARSHAD KAPOORSTEVE BARRDAVID BAVERMIKE DISORICHRIS GUMKE

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3-VIEW

FRONT VIEW

4.5 ft.

3

2°

TOP VIEW

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7 ft.

10 ft.

3 ft.

46 ft.

3.5 ft.

2 ft.

8 ft.

1 ft.

SIDE VIEW

5CG. Location .35c and Neutral Point location at .44c

3 ft.

13.3 ft.

4 ft.

6.5 ft.6.25

ft. 2 ft.2.5 ft.

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%

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SIDE VIEW

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STABILITY AND CONTROL

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Component Weight of Part (lb.) CG location from nose (ft.)Passengers 400 8.2Batteries 400 3.5

Motor 42 12Controller 30 2Propeller 15 10

Seats 40 0.5Tail 60 8.2

Fuselage + Wing 313 7.5

Forward limit CG location Aft limit Static Margin6.40 8.21 8.61 9%

SPECIFICATIONS

Parameters Value

Power Available (hp) 80.0

Engine Efficiency 0.90

Max Propeller Efficiency 0.87

Cabin Width (ft) 5.00

Vertical Tail Height (ft) 4.50

Base Vertical Tail Chord (ft) 4.00

Tail Chord (ft) 2.00Tail Span (ft) 8.00

Span Efficiency of Tail 0.95

Parameters Value

Weight (lbs) 1300

Span (ft) 46.0

Root Chord (ft) 3.50

Tip Chord (ft) 3.00

Wing Area (ft^2) 156

Wing Loading (lb/ft^2) 8.30

Aspect Ratio 13.6

Taper Length (ft) 10.0

Taper Ratio 0.94

Span Efficiency 0.969

AILERON SIZING

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Aileron Sizey2 22 ft

y1 12 ft

Roll Rate 45 deg/sec

y2

y1

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Vertical Tail SizingEstimated Side Wash

Parameter * 0.17

Effective Tail Parameter 0.7

Vertical Tail Lift Slope 6.25/rad

Vertical Tail Volume 0.026

Weathercock Stability -0.04

Rudder Power -0.051Rudder Deflection @ Max Sideslip ** 9.12°

* Ideal Side Wash Parameter from Morelli Paper** IAW FAR Section 23 – Max sideslip for crosswinds is 11.5°

VERTICAL TAIL

TURN PERFORMANCE(BASED ON AERODYNAMIC PARAMETERS)

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FAR Allowable Range: -1.5G to 3.8G

CABIN DRAWING

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POWERPLANT AND BATTERIES

ENGINE:YUNEEC POWER DRIVE 60

POWER:81 HP

OPTIMUM RPM:2,400

WEIGHT:66 LBS

BATTERY ENERGY DENSITY: 240 WHr/Kg

BATTERY WEIGHT: 400 LBS

BATTERY EFFICIENCY: 0.90

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WING AIRFOILNLF 0115

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HORIZONTAL & VERTICAL TAIL AIRFOIL

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EPPLER 521

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TOTAL DRAG BUILD-UP

Airspeed (kts)

Landing Gear (lbs)

Fuselage Drag (lbs)

Wing Drag (lb)

Empennage Drag (lbs)

Total Drag(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

TOTAL DRAG BUILD-UP

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TotalInducedProfile

LIFT TO DRAG RATIO

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MAX L/D = 32@ 65 KNOTS

POWER REQUIRED AND AVAILABLE VS. VELOCITY

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ftft

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

STALL SPEED

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LIFT CURVE

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ENDURANCE AND RANGE

• C = BATTERY ENERGY DENSITY• WB = BATTERY WEIGHT

• ηB = BATTERY EFFICIENCY

• ηC = CONTROLLER EFFICIENCY

• ηB = PROPELLER EFFICIENCY

• Preq = POWER REQUIRED• V = VELOCITY

ENDURANCE: RANGE:

E = 2.5 HOURS & R = 220 MILES@ SEA LEVEL, CRUISE SPEED

E = 3.5 HOURS & R = 360 MILES@ SEA LEVEL, CRUISE SPEED WITH

EXTENDED BATTERY PACK

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TAKE-OFF AND LANDING DISTANCES

GROUND ROLL:

SGROUND ROLL = 315.61 FT

LANDING DISTANCE:

SLANDING = 1341.85 FT

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V-n Diagram

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WEIGHT AND COST ESTIMATION

Engine, Motor, and Battery SystemComponent Weight (lbs) Cost ($) # of Parts Total Weight(lb) Total Cost ($)

Propeller 15 2500 1 15 2500Electric Engine (80HP) 42 8200 1 42 8200Battery Pack (Li Ion) 191 900 2 382 1800Power Block 40 Controller 15.5 1789 1 15.5 1789

E Charger 15.4 900 1 15.4 900Electric Wiring System 1.9 400 4 7.6 1600Engine Cowling 20 1300 1 20 1300Spinner Cover 1 340 1 1 340Section Total: 498.5 18429

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WEIGHT AND COST ESTIMATION

Cockpit Fuselage, Instruments and Controls

Component Weight (lbs) Cost ($) # of Parts Total Weight (lbs) Total Cost ($)

Aircraft Seats 20 100 2 40 200Instrument Panel 19.5 6138 1 19.5 6138Flight Controls 2 140 2 4 280Canopy 10 1469 1 10 1469Restrain Belts 4 80 2 8 160Rudder Pedals 2 229 2 4 458Flight Control Linkages 25 1900 1 25 1900Composite Skin/ Fuselage 45 2800 1 45 2800Passengers 200 0 2 400 0Section Total: 555.5 13405

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WEIGHT AND COST ESTIMATION

Wing, Ailerons, and Structure

Component Weight (lbs) Cost ($) # of Parts Total Weight (lbs)

Total Cost ($)

Composite Wing, Aileron, and Skin Structures 146 9100 1 146 9100

Aifrcraft Lights 0.5 120 4 2 480Section Totals: 148 9580

Empennage and Tail Boom

Component Weight (lbs)

Cost ($)

# of Parts

Total Weight (lbs)

Total Cost ($)

Composite Tail Boom, Horizontal and Vertical Tail, and Skin/ Structure

60 3800 1 60 3800

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WEIGHT AND COST ESTIMATION

Forward and Main Landing Gear, Tires, and Wheel Pants

Component Weight (lbs)

Cost ($)

# of Parts

Total Weight (lbs)

Total Cost ($)

Landing Gear Struts 3 140 3 9 420Tires 4 114.95 3 12 344.85Wheel Pant Composite Skin 1 70 3 3 210Section Totals: 24 974.85

Overall System Totals:

Cost ($) 46k

Weight (lbs) 1286

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• Environmentally Friendly• Cost Effective– Low Operating Costs– Low Unit Cost

• iPad integrated• Quiet• Trainer Aircraft– Easy Learning Curve

• Excellent Maneuverability

KEY POINTS

• Modern Instrument Panel• LSA Certifiable• Lightweight Composite Design• Laminar Flow Airfoil– Low Drag

• FUN

KEY POINTS

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QUESTIONS