X-006 Mana Simo

AlbertiPresenting to BoeingHuntington Beach CANovember 20th , 2009

Design Goal

•Make an efficient next generation aircraft

•Include aggressive futuristic advance technologies

•Maintain a familiar and conventional shape

Alberti - 2

CONOPS•Max range 3500 nautical miles

▫Including climb and descent NYC to Milan, Italy LA to Caracas, Venezuela Miami to Santiago, Chile

•Mach 0.8 cruise at 35,000 ft•45 min loiter at 1,500 ft•200 nautical mile divert, Mach 0.582 at

15,000 ft

Alberti - 3

Advanced Technologies•Hybrid laminar flow control

▫75% chord laminar flow▫50% reduction in CD,0

•Windowless fuselage▫Improved pressure vessel, less weight

•Geared turbofan – PW1000G▫> 20% fuel burn reduction

•BL ingesting unducted fan▫~ 26% fuel burn reduction

Alberti - 4

Fuselage Trade StudyFuselage 3-3 2-2-2 2-4-2

Dimensions w: 12.5’h: 15’l: 117’

w: 15.5’h: 15.5’l: 105’

w: 16’h: 16’l: 90’

Cost 20 2 3 1

DragCD

30 10.0062

20.0066

20.0067

Comfort/Space 10 3 1 2

Windowless 10 3 2 1

Stretchability 15 3 2 1

Loading Time 10 3 1 2

Innovation 5 2 1 1

100

57.5/100 59/100 75/100

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Engine Trade Study

Engine Cycle CFM UDF

CFM LeapX

PW1000G

RB2011

Readiness 5 4 2 1 4

Fuel Burn 35 1 4 2 3

Noise 20 4 1 1 3

Emissions 10 1 1 1 1

Thrust Range

5 2 2 1 2

Future 15 1 4 2 1

Weight/Size 10 3 2 1 3

100

72/100 52.5/100 75/100 50.5/100

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Engine Layout ChoiceEngine Count Engine Location

•2 Engines▫Symmetric

configuration▫More thrust required

•3 Engines▫Easier OEI

requirements▫Lower T/W▫More maintenance &

cost

•Under Wing▫Easy for maintenance

•Over Wing▫Emergency

complications•TE of fuselage

▫BL propulsion▫Improved thrust▫~ 10% reduction of

turbulent fuselage drag

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2 Turbofans + 1 Unducted Fan

•UDF provides better thrust at sea level▫Reduced OEI constraints

•Turbofan provides better thrust at altitude▫Reduced service ceiling constraint

•1/3 of total thrust provided by UDF▫Weight reduction of ~ 7 %▫Fuel weight reduction of > 17%

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Thrust Lapse TSFC

Unducted Fan 0.233 0.458

Turbofan 0.300 0.699

1/3 UDF Hybrid 0.278 0.578

Modified engine deck

•Thrust ratio,

•Thrust lapse,

•Specific fuel consumption,

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sls T

T =

Total

UDF

UDFGTF + )-(1=

+ )-(1

TSFC +TSFC )-(1 =TSFC

UDFGTF

UDFUDFGTFGTF

40 60 80 100 120 140 1600

0.05

0.1

0.15

0.2

0.25

0.3

0.35

0.4

Wing Loading (lbf/ft2)

Th

rust

to W

eig

ht R

atio

Service Cieling - 500ft/minTakeoff Distance - 8200ft

Approach Speed - 140 kts

Sea Level Climb - 2100ft/min

OEI Climb - 400ft

OEI Climb - 1500ftAEO - Approach Climb

Constraint Diagram

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80 90 100 110 120 130 140 150

0.16

0.18

0.2

0.22

0.24

0.26

Wing Loading (lbf/ft2)

Th

rust

to W

eig

ht R

atio

80 90 100 110 120 130 140 150

0.16

0.18

0.2

0.22

0.24

0.26

Wing Loading (lbf/ft2)

Th

rust

to W

eig

ht R

atio

80 90 100 110 120 130 140 150

0.16

0.18

0.2

0.22

0.24

0.26

Wing Loading (lbf/ft2)

Th

rust

to W

eig

ht R

atio

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80 90 100 110 120 130 140 150

0.16

0.18

0.2

0.22

0.24

0.26

Wing Loading (lbf/ft2)

Thr

ust

to W

eigh

t R

atio

1/3 thrust from UDF

Service Cieling - 500 ft/min

Takeoff Distance - 8200 ft

Approach Speed - 140 kts

OEI Climb - 400 ft

OEI Climb - 1500 ft

AEO - Approach Climb

Legend

100 % Turbofan

100% Unducted Fan

Hybrid Propulsion

Design PointWing

LoadingThrust to

WeightTake off Weight

Empty Weight

Fuel Weight

145 0.25 146,000 73,000 36,000

120 0.21 142,000 71,000 34,000

106 0.18 145,000 72,000 35,000

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• W/L: 120 lb/ft2

▫Optimal CL for L/D▫118 ft span, max for FAA class III

• T/W: 0.21▫11,000 lbf per engine▫High bypass, only 4.6’ diameter fan

Aircraft Sizing• Max take off weight: 142,000 lb• Empty weight: 71,000 lb• Fuel weight: 34,000 lb• Payload weight: 37,000 lb

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% of fuel

3-View -change

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92 ft

45 ft

118 ft

Wing•Hybrid Laminar Flow Control

▫Leading edge suction▫Suction powered by jet engines▫NLF supercritical airfoil▫Objective:

75% laminar flow over wing and tail▫L/D improvement of > 55%

•Area: 1300 ft2

•Span: 118 ft•Chord: 9.1 ft•AR: 12•Sweep: 25˚

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V Tail•Improve boundary layer ingestion region

•Cleaner flow to unducted fan▫More efficient propulsion

•Reduced wetted surface▫Reduced drag▫Simplified HLF

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Aerodynamic Analysis

•Max L/D▫CL = 0.52

▫L/D = 24.4 laminar

▫L/D = 18.7 turbulent

•Cruise▫CL = 0.54

▫L/D = 24.4

•Transonic Drag Rise▫MDD = 0.82

▫Mcrit = 0.71

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0 0.01 0.02 0.03 0.04 0.05 0.060

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1Drag Polar

Drag Coefficient

Lift

Co

effi

cie

nt

w/ HLFw/o HLF

Parasite Drag Buildup

Alberti - 18

•CD = 110 counts

Effect of HLFC on Drag

X63T18S Airfoil•Super critical LFC airfoil

▫Combined with LE suction▫Kruger deicing and

flyspeck protection device•Shock-free airfoil design•High design mach number

▫Lift generated in front and rear sections

▫Low supersonic flat rooftop

•Low sweep to prevent crossflow contamination

•Double slotted flaps

Alberti - 19

NASA - W. Pfenninger

Alternative Fuels

Biofuels Hydrogen• Lower energy density• Huge infrastructure

requirement▫ Impossible by 2020

• Unpredictable costs

• 143 MJ/kg – 3.3 times higher than kerosene▫ Could fly with 10,000 lb

• 10,000 psi or 36 ˚R storage

• Works with Brayton cycle

• 2% of emissions due to aviation, 40% due to automotive

• Need for high performance, low weight fuels• Hardest challenge with small reward

• Alternative Approach• Improve fuel burn in mission• Evolve ground vehicles to 21st century

technology

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Noise and Emissions•Unducted Fan

▫Rolls-Royce claims, UDF quieter than turbofan

▫Aft location, far from passengers▫Reduced emissions

•PW1000G▫-15 db noise improvement▫COx reduction of 20%▫NOx reduction of 50%

•Windowless Design▫Better acoustic shielding

Alberti - 21

Hackmod.com

Ground Integration

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Questions?

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