Team 3 Marques Fulford Mike Bociaga Jamie Rosin Brandon Washington Jon Olsten Tom Zettel Hayne Kim

2 Review of Mission Walk-Around Diagrams Design Goals Compliance Sizing Methods and Results Design Trade-offs and Visualization Analysis Aerodynamics Propulsion Performance Structures Weights & Balance Stability & Control Aircraft Servicing Environmental Impact Outline

3 Relieve continuously growing congestion of large hubs Utilizing secondary airports with ESTOL Performing half-runway takeoffs Non-interfering spiral decent landings Short – Medium range 2000 nmi Mission Review Mission Goal

4 Gary Chicago to Dallas Love Field 693 nmi New York LaGuardia to Miami International 935 nmi Charlotte International to Essex County, NJ 460 nmi Round trip without refueling Mission Review Use-case Scenarios

5 Geared Turbofan Engine Forward Swept Wing Upper Surface Blowing Composite Fuselage Advanced Integrated Flight Deck Extra Large Cabin Windows Walk-Around Exterior

66 Hydrogen Fuel Cell APU 50gal Potable Water Tank Hydrogen Fuel Tank Jet Fuel Wing Tank Baggage Compartment Nose GearMain Gear Walk-Around Concealed Components

7 Requirements TargetThresholdCurrent Takeoff Runway Length ≤ 2500ft3000ft1490ft Landing Runway Length ≤ 2500ft3000ft1690ft Height to Passenger Door Sill at OWE ≤ 5ft9 8.2ft Height to Baggage Door Sill at OWE ≤ 4ft6 5.2ft Typical Cruise Mach Number ≥ Range w/ Max Payload ≥ 2000nmi1500nmi3000nmi Max Take-Off Weight ≤ 100,000lb150,000 lb86,800lb Max Passengers (single class) ≥ 170pax150pax177pax Operating Cost ($US 2007) ≤ 0.08$/ASM0.12$/ASM unavailable $/ASM Compliance Matrix

8 Fixed Parameters Value C L,max 4 t/c0.11 Λ at.25c (forward) 25° λ0.278 AR10 Sizing Fixed Design Parameters

9 Sizing Carpet Plot W/S = 84 lb/ft 2 T/W=0.310 Ground Roll <= 1500ft

10 Sizing Methods and Flowchart Yes No 1,2 Empty Weight Fraction, Component Weights estimated from methods in “Aircraft Design: A Conceptual Approach” by Daniel P. Raymer Approach validated with 737 dataApproach validated with 737 data Produced sizing results for three mission cases and target and threshold range casesProduced sizing results for three mission cases and target and threshold range cases Aircraft sized to worst-case resultAircraft sized to worst-case result 2000 nmi Target Range2000 nmi Target Range Input: Fixed Design Parameters Size Aircraft Weight, Surfaces, Fuel Empty Weight based on Component Weight 2 Empty Weight s Agree? Final Sizing Results Empty Weight Fraction Estimation 1

11 Horizontal TailHorizontal Tail Sized to provide moment to meet take-off rotationSized to provide moment to meet take-off rotation Vertical TailVertical Tail Sized provide one-engine out performance requirement with 20 degrees of rudder deflectionSized provide one-engine out performance requirement with 20 degrees of rudder deflection Sizing Vertical, Horizontal Tails

12 Sizing Tail Sizing Fixed Parameters Vertical Tail Parameters Value Moment Arm [ft] 40 AR1.56 λ0.31 Λ at.25c 35° Horizontal Tail Parameters Value Moment Arm [ft] 40 AR5.54 λ0.186 Λ at.25c 30°

13 Sizing Results WeightsValue TOGW [lbs]86,800 We [lbs]35,000 Gross Landing Weight [lbs]76,350 We/Wo0.403 Fuel Weight [lbs]11,680 Aircraft DimensionsValue Wingspan [ft]102 Wing Area [sq. ft]1,032 Wing Mean Aero. Chord [ft]11 Vertical Tail Height [ft]23 Vertical Tail Area [sq. ft]350 Horizontal Tail Span [ft]66 Horizontal Tail Area [sq. ft]450 Fuselage Length [ft]123

14 Wing moved slightly forward to reduce vertical tail sizeWing moved slightly forward to reduce vertical tail size Loss of 4 degrees of rotation on takeoffLoss of 4 degrees of rotation on takeoff Tail-strike at 14 deg rotationTail-strike at 14 deg rotation Canard replaced by Conventional TailCanard replaced by Conventional Tail Avoid “ramp rash”Avoid “ramp rash” Stability – simplicityStability – simplicity Design Trade-Offs

15 Design Front View 102 ft 18.5 ft 32 ft

16 Design Side View 123 ft 10 ft 63 ft 35ft V. Tail Area: 350 sq ft

17 Design Top View 16ft Fuselage Width: 12ft 4in 40ft H. Tail Area: 450 sq ft Wing Area: 1032 sq ft

18 First Class: 35” Seat Pitch 16 Passengers Economy Class: 32” Seat Pitch 147 Passengers Economy Lavatories First Class LavatoryFirst Class Galley First Class Galley Emergency Exit Rows 36” Seat Pitch Design Two-Class Interior – 163 Total Passengers

19 Forward Lavatory Forward Galley Rear Lavatories Rear Galley Emergency Exit Rows 36” Seat Pitch All Economy 32” Seat Pitch 177 Passengers Design Single-class Interior – 177 Total Passengers

20 Aerodynamics Airfoil Selection Supercritical airfoils from a Gulfstream GIII selected as representative of a future airfoil selectionSupercritical airfoils from a Gulfstream GIII selected as representative of a future airfoil selection GIII Root Airfoil Potential Flow GIII Mid-Span 2D Airfoil C l vs. AOA

21 Aerodynamics Airfoil Selection Airfoil section for Vertical and Horizontal tails based off of operational needs of tail componentsAirfoil section for Vertical and Horizontal tails based off of operational needs of tail components Symmetric airfoil sections usedSymmetric airfoil sections used

22 Continuous flap section where USB has significant impact (inboard)Continuous flap section where USB has significant impact (inboard) Double-slotted Fowler Flaps where USB effect is negligible (outboard)Double-slotted Fowler Flaps where USB effect is negligible (outboard) Aerodynamics High Lift Devices

23 Major Aerodynamic Features: Fuselage Wing Vertical Tail Horizontal Tail Engine Nacelle Smoothness of Composites reduces Skin Friction, helps maintain laminar flow over a larger section of fuselage, wings C D0 ≈ Aerodynamics Parasite Drag Buildup

24 Parasite, Induced, and Wave Drag Aerodynamics Aircraft Drag Polar

25 To take off with one engine out: Max Thrust (ea.): lbs Weight (ea.):~ 4300 lbs SFC (cruise): 0.36 hr -1 Mounted above the wing Upper surface blowing to increase C L,max Turbo-Fan analysis in Hill & Peterson 1 used to evaluate engine performance Bypass Ratio: 12 Fan Pressure Ratio:1.5 Compressor PR:20 Propulsion Geared Turbo-Fan 1 “Mechanics and Thermodynamics of Propulsion” by Hill & Peterson

26 Altitude: 30,000 ft V stall 129 kts V max 493 kts V best range 408 kts Cruise Propulsion Thrust, Drag vs. Velocity V best range M = 0.78 Altitude: 36,000 ft V stall 144 kts V max 488 kts V best range 482 kts

27 Cruise Altitude: 36,000 Feet Stall Limit Absolute Ceiling: 51,000 Feet Service Ceiling: 46,000 Feet Performance Flight Envelope

28 Stall Speed = 85 knots Corner Speed = 147 knots Cruise Speed = 447 knots Dive Speed = 559 knots Performance V-n Diagram

29 Best Range Velocity: 482 knots Best Endurance Velocity: 375 knots Maximum Speed: 488 knots (36,000ft) Stall Speed: 85 knots Takeoff Speed: 94 knots Approach Speed: 128 knots Total Takeoff Distance: 2600 ft Total Landing Distance: 2400 ft (5,000ft) Performance Characteristics

30 Carbon Fiber Reinforced Plastic High Strength Low Weight 25%+ weight savings over current material For aircraft 80% composites by weight Cost will decrease as use becomes commonplace Fiber Optic Cable (Fly-by-light) Faster & lighter than copper Cheaper to maintain Structures Material Selection

31 Main Wing Spars Landing Gear Kick Spar Wingbox Carrythrough Wing Ribs Engine Mount Structures Wing Structure Configuration

32 StructuresWeight (lbs) Wing5911 Horizontal Tail704 Vertical Tail785 Fuselage5173 Main Landing Gear2519 Nose Landing Gear353 Nacelles2260 PropulsionWeight (lbs) Engine Installed8600 Engine Control104 Starter158 Fuel System / Tanks244 EquipmentWeight (lbs) Flight Controls1103 Installed Fuel Cell (APU)2323 Instruments356 Hydraulics299 Electrical186 Avionics124 Furnishings502 Air Conditioning934 Anti-ice156 Handling Gear23 Useful LoadWeight (lbs) Aircraft Empty34980 Crew1200 Fuel11680 Payload38940 Weight and Balance Component Weight

33 Weight and Balance Stability and Static Margin Weight (lbs) CG location Static Margin (%) Aircraft Empty Empty + Crew Empty + Crew + Fuel Takeoff Landing

34 Center of Gravity Neutral Point Aircraft Length: 123 ft Forward C.G: 65.4 ft Takeoff:69.9 ft Aft C.G: 70.5 ft Neutral Point:70.5 ft (MTOW) Weight and Balance Stability and Static Margin

35 Rotation Angle = 10 deg Horizontal Tail Area = 450 ft 2 One engine out condition Vertical Tail Area = 350 ft 2 Weight and Balance Control Surface Sizing Rudder Deflection (deg) Rudder Size (ft^2) Area Percentage Elevator Deflection (deg) Elevator Size (ft^2) Area Percentage

36 Aircraft Servicing Conventional Terminal Servicing Terminal Servicing without use of APU Compatible with airports that are using current equipment

37 Servicing Using Hydrogen Fuel Cell APU Hydrogen Fuel Truck hookup No Environmental impact No Waste Less Equipment Could potentially eliminate potable water truck Aircraft Servicing Hydrogen Fuel Cell Terminal Servicing

38 Advantages of Design Easy access to engine core Easy removal of engine core Overwing access to engine Disadvantage Higher off ground than underwing engine 38 Aircraft Servicing Engine Maintenance

39 Environmental Impact Emissions and Waste Reduced SFC Less fuel burn, emissions Composite Construction Less material use, waste Hydrogen Fuel Cell APU No toxic emissions Quieter Engines Reduced noise pollution

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