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Mission Statement
Market
Competition
Concept of Operations
Design Requirements
Design Comparison
New Technologies and Advanced Concepts
Sizing Code
Summary
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To design an environmentally responsible
aircraft for the twin aisle commercial transport
market with a capacity of 300+ passengers,
NASA’s N+2 capabilities, and an entry date of
2020-2025.
NASA’s N+2 technology benefits include:
 Reducing cumulative noise by 42dB below Stage 4
 Reducing take-off and landing NOx emissions to 75% below
CAEP6 levels
 Reducing fuel burn by 50% relative to “large twin-aisle
performance” (777-200LR)
 Reducing field length by 50% relative to the
large twin-aisle
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 Twin-aisle aircraft
represent the fastestgrowing market segment
 Growth fueled by
emerging economies
(Asia-Pacific, Latin
America, Middle East,
etc.)
Image Source:
Boeing Market Forecast
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 Asia-Pacific, Middle East, Latin America
 Low Cost Carriers (LCC’s)
 Passengers looking for cheap hub-to-hub
and nonstop flights
 Airliners looking for high capacity aircraft
to meet increasing market demand
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 High-Speed Rail Systems
Map of proposed
high-speed rail
systems in China,
along with estimated
travel times from
Beijing
Image Source:
www.hasea.com
 Boeing 737, Airbus A319
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 Operational City Pairs
Runway Length (ft)
Origin
Destination
Tokyo,
Japan
Seoul,
South Korea
Sydney,
Australia
Beijing,
China
Hong Kong,
China
Tokyo,
Japan
Sapporo,
Japan
Jeju,
South Korea
Melbourne,
Australia
Shanghai,
China
Taipei,
Taiwan
Naha,
Japan
Reference: Centre for Asia Pacific Aviation
Origin
Flight Time (Min)
Route
Destination Distance
(nmi)
0.75
Mach
0.85
Mach
8,202
9,843
593.91
101.91
93.45
10,499
9,843
323.86
69.21
64.60
8,301
11,998
509.89
91.73
84.47
10,499
10,827
779.22
124.35
113.25
12,467
10,991
580.10
100.24
91.97
8,202
9,843
803.39
127.27
115.83
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 Design Mission
 400 Passengers (Max Payload)
 4,000 nmi Range
(Tokyo-NHD to New Delhi-DEL: 3,200nmi)
 Runway Length
 8,300 ft (Takeoff)
4000 nmi
200 nmi
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Requirement
Threshold
Target
Cruise Mach
0.75
0.85
Range
3,000 nmi
4,000 nmi
Field Length
8,300 ft
5,800 ft
Fuel Burn
33% reduction
50% reduction
NOx Emissions
50% below CAEP 6
-32 dB
(cum. below Stage 4)
350
75% below CAEP 6
-42 dB
(cum. below Stage 4)
400
Noise Reduction
Pax Capacity
*Reference Vehicle B737-700
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Requirement Target Design B767-300
B777-200
B737-700
Cruise Mach
0.85
0.85
0.84
0.785
Range
4,000 nmi
3,780 nmi
5,240 nmi
3,440
Field Length
5,800 ft.
7,907 ft.
8,202 ft.
8,300 ft.
Pax Capacity
400
350
440
149
Reference: Boeing.com
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PROPULSION
 Geared Turbofan
 Unducted Fan (UDF)
 Bio-Diesel
AERODYNAMICS
 Trailing Edge Brushes
 Blended Wing Body
 Spiroid Winglets
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DYNAMICS & CONTROLS
 Fly By Wireless
 Morphing Trailing Edge
STRUCTURES
 Composites
 Bonded Skin Panels
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 We used three sizing codes:
 Simple – Incorporates design mission range, (L/D)max and
number of passengers
 Initial – Incorporates all of the above in addition to T/W and W0/S
ratios.
 MATLAB – Incorporates all of the above and the entire design
mission (i.e. loiter time, emergency landing etc.)
Boeing 767 - 200ER with CF6-80C2B7F engines:
W 0 (Maximum Takeoff Gross Weight) [lb]
W e (Empty Weight) [lb]
W f (Fuel Weight) [lb]
Airbus A330 - 200 with CF6-80E1A2 engines:
W 0 (Maximum Takeoff Gross Weight) [lb]
W e (Empty Weight) [lb]
W f (Fuel Weight) [lb]
Sizing codes used
Simple
Initial
MATLAB
Actual Calculated Error Calculated Error Calculated Error
395,000
383,375 -2.94% 389,861 -1.30% 546,580 38%
184,400
195,300 5.91% 202,484 9.81% 252,340 37%
122,275
121,576
243,550
Simple
Initial
MATLAB
Actual Calculated Error Calculated Error Calculated Error
507,050
493,299 -2.71% 502,105 -0.98% 563,040 11%
263,075
241,182 -8.32% 256,006 -2.69% 259,480
-1%
176,216
170,198
245,840
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 Market forecasts predict a need for higher capacity
aircraft to fly heavily trafficked routes
 400 passenger, 4000 nmi range, N+2 compliant aircraft
scheduled for deployment in 2020-2025
 Next Steps




Constraint Analysis
Sizing code refinement
Acquire Propulsion systems data
Preliminary wing design
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