Logan Waddell Morgan Buchanan Erik Susemichel Aaron Foster Craig Wikert Adam Ata Li Tan Matt Haas 1

Outline I. Mission Statement II. Market and Customers a. Market size b. Customer Benefits / Needs III. Competition IV. Concept of Operations a. Representative City Pairs b. Payload / Capacity c. Design Mission V. System Design Requirements a. Design Requirements b. Benchmarking VI. Technologies / Advanced Concepts VII. Initial Sizing 2

Mission Statement  To design an environmentally responsible aircraft that sufficiently completes the “N+2” requirements for the NASA green aviation challenge.  “N+2” Goals ○ Burn 50% less fuel burn ○ Cumulative -42 dB noise reduction (Approach, Landing, Taxi) ○ 75% reduction in LTO nitrogen oxide emissions 3

Customer Needs / Benefits  NASA ○ “N+2” goals  Airlines  General Public 4 Airport Noise levels

Market / Customers *Boeing 5 Twin Aisle - Value ($B) ~3,600 Twin Aisle – 7,100 new airplanes Boeing projects the worlds fleet to double by 2029

Market / Customers 6 *Boeing Steady increase in RPK since 1977, ~ 5% annually Largest Markets: Asia-Pacific, North America, Europe

Competition  Similar size aircraft: ○ Boeing , , 787 ○ Airbus A  High speed rail ○ Bullet trains 7 Boeing 757 and 767

CONOPS - City Pairs  Mission design represents popular routes Examples Routes Great Circle Distance Passengers / Year ____________________________(nm)__________________________  Domestic range requirement of 3200 nm based on: MIA to SEA facing 65 kts headwind FAR Reserves LondonNew York MiamiSeattle2363 N/A New YorkSan Francisco Los AngelesNew York MiamiNew York AtlantaNew York ChicagoNew York Las VegasLos Angeles BostonNew York

Runway Length *MIT AirportRunway lengths (ft) JFK14572 ORD13001 LAX12091 SFO11870 LHR12799 LAS14510 MIA13000 ATL11890 BOS10083 SEA

Aircraft Payload / Passenger Capacity  250 Passengers 180 lb/passenger Baggage 50 lb/passenger On board Baggage 15 lb/passenger  7 Crew Members 180 lb/crew Baggage 30 lb/crew W payload = lbs W crew = 1470 lbs 10

Design Mission 11

Typical Operating Mission Typical Design Missions Aircraft QualitiesAircraft LimitationsTypical Design Mission Range4,000 nm750 nm City PairsSeattle to MiamiChicago to New York Passengers Cruise Altitude35,000 ft30,000 ft Reserve Segments200 nm100 nm Takeoff Weight268,000 lbs243,100 lbs Mach Number0.8 12

Design Requirements Compliance Matrix RequirementUnitTargetThresholdCurrent Rangenaut. miles Payloadpax Cruise Mach # Runway Length (Takeoff)ft Runway Length (Landing)ft Emissionsg/kN thrust1522- Noise (Cum.)dB Fuel Burn (SFC)-Cruiselb/(lbs*hr)

Design Requirements Noise (below stage 4) -42 dB LTO NO x Emissions (below CAEP 6) -75% Performance: Aircraft Fuel Burn -50% Performance: Field Length -50% ERA N+2 Requirements  Noise prediction/reduction technologies for airframe/propulsion systems  Emissions-reduction technologies (mainly NO x )  Alternative Fuel Usage  Improved vehicle performance from: Lightweight, durable structures High-lift aerodynamics Higher bypass ratio engines NASA Subsonic Fixed Wing Project Goals: 14

Benchmarking Max Passengers OEW (lb) Max Takeoff Weight (lb) Max Payload (lb) Usable Fuel (lb) Cruise Mach # Max Field Length (ft) Max Range (nmi) Boeing PF279142,350270,00038,20079, ,5004,750 Boeing ER255181,610395,00078,500161, ,0006,385 Boeing LR301320,000766,000141,000320, ,0009,395 Airbus A ,527187,39354,00051, ,0003,200 Airbus A ,845480,607115,01297, ,0007,250 Info on Boeing aircraft from boeing.com Info on Airbus aircraft from airbus.com 15

Technologies/Advanced Concepts  Fuel Burn  Spiroid winglets  Advanced engine concepts  Noise  Landing gear  Emissions  Less fuel burn 16

Technologies/Advanced concepts  Winglets ○ Blended ○ Spiroid ○ Multi-Winglets 17

Geared Turbofan Engine  Pratt & Whitney currently has a line of geared turbofan engines called the PurePower family. Developing advanced GTF for Airbus and Boeing next gen narrow body replacement aircraft.  Geared Turbofan allows fan to operate at lower speeds while compressor and turbine operate at high speeds.  Provides 12%-15% improvement in fuel burn range, 50% NOx emissions reduction, and 20 dB decrease from CAEP noise standards 18

Affordable Large Integrated Structures  Eliminates structural discontinuities and fastened assemblies  Reduction in part count  Lower manufacturing time and cost 19 Northrop Grumman

Landing Gear Fairings  Reduces the noise in the mid and high frequency domain compared to the plain landing gear configuration up to 4.5 dB  Reduces vortex shedding due to bluff-body nature of nose and main landing gear Northrop Grumman 20

Hybrid Laminar Flow Control 21 Active drag reduction technique Design of the suction surface Chambers underneath the perforated skin Applied to the vertical and horizontal tail reduces drag by 1% *Clean Sky

Composite Materials  Lighter weight ○ High strength to weight ratio ○ Reduction of overall weight 20% or more  Stronger ○ Graphite/epoxy composite ○ Greater resistance to damage from cyclic loading  Hybrid ○ Addition of fiberglass or kevlar ○ Creates greater fatigue toughness ○ Impact resistance 22

Sizing Using MATLAB to create a comprehensive sizing code based on first order method from Raymer text Empty weight prediction based off of Raymer database (Table 3.1) Equation Used: W e /W 0 =A*W 0 C *K vs Fuel weight prediction based on drag and fuel burn predictions Climb, Landing, Warmup and Takeoff fractions used historical data Cruise fraction used Breguet range equation: exp(-R*C/(V*L/D)) Loiter fraction used endurance equation: exp(-E*C/(L/D)) L/D prediction Equation Used: L/D = 1.4*AR

Aircraft Database Published Information (from Jane’s All the Worlds Aircraft and Boeing.com) Boeing ERAirbus A Range6,545 [nmi]6,750 [nmi] Takeoff Gross Weight395,000 [lb]507,050 [lb] Empty Weight (OWE)184,400 [lb]263,075 [lb] Fuel Weight159,920 [lb]186,255 [lb] Total Fuel capacity23,980 [gal]36,750 [gal] Boeing ERAirbus A

Sizing Code Predictions ActualPrediction% Error Gross Takeoff Weight 395,000 [lb]408,264 [lb]3.35 Empty Weight Fraction L/D (cruise) ActualPrediction% Error Gross Takeoff Weight 507,050 [lb]365,624 [lb] Empty Weight Fraction L/D (cruise) N/A Boeing ERAirbus A The initial sizing calculations prove to be mostly accurate on both of the baseline aircraft 25

Our Design Predictions Prediction Gross Takeoff Weight267,365 [lb] Empty Weight128,848 [lb] Empty Weight Fraction

Summary and Next Steps  Finalizing the sizing code  Including the new technologies into the sizing  Constructing a preliminary CAD geometry for the aircraft 27

References  Boeing  Airbus  NASA  MIT  Northrop Grumman  Aviation Week  Perforated Fairings for Landing Gear Noise Control, N. Molin 28