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Aircraft Design for Boeing Phantom Works
 

Aircraft Design for Boeing Phantom Works

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Personal aircraft design interpretation of AIAA competition presented to Boeing Phantom Works, Huntington Beach, CA

Personal aircraft design interpretation of AIAA competition presented to Boeing Phantom Works, Huntington Beach, CA

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  • Simo Alberti
  • 18% more weight 40% more fuel Simo Alberti

Aircraft Design for Boeing Phantom Works Aircraft Design for Boeing Phantom Works Presentation Transcript

  • X-006 Mana Simo Alberti Presenting to Boeing Huntington Beach CA November 20 th , 2009
  • Design Goal
    • Make an efficient next generation aircraft
    • Include aggressive futuristic advance technologies
    • Maintain a familiar and conventional shape
    Alberti -
  • 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 -
  • Advanced Technologies
    • Hybrid laminar flow control
      • 75% chord laminar flow
      • 50% reduction in C D,0
    • Windowless fuselage
      • Improved pressure vessel, less weight
    • Geared turbofan – PW1000G
      • > 20% fuel burn reduction
    • BL ingesting unducted fan
      • ~ 26% fuel burn reduction
    Alberti -
  • Fuselage Trade Study Alberti - Fuselage 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 Drag C D 30 1 0.0062 2 0.0066 2 0.0067 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
  • Engine Trade Study Alberti - 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
  • Engine Layout Choice
    • Engine 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
    Alberti -
  • 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%
    Alberti - 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,
    Alberti -
  • Constraint Diagram Alberti -
  • Alberti - Legend 100 % Turbofan 100% Unducted Fan Hybrid Propulsion
  • Design Point Alberti -
    • W/L: 120 lb/ft 2
      • 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
    Wing Loading Thrust to Weight Take 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
  • Aircraft Sizing
    • Max take off weight: 142,000 lb
    • Empty weight: 71,000 lb
    • Fuel weight: 34,000 lb
    • Payload weight: 37,000 lb
    Alberti - % of fuel
  • 3-View -change Alberti - 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 ft 2
    • Span: 118 ft
    • Chord: 9.1 ft
    • AR: 12
    • Sweep: 25˚
    Alberti -
  • V Tail
    • Improve boundary layer ingestion region
    • Cleaner flow to unducted fan
      • More efficient propulsion
    • Reduced wetted surface
      • Reduced drag
      • Simplified HLF
    Alberti -
  • Aerodynamic Analysis
    • Max L/D
      • C L = 0.52
      • L / D = 24.4 laminar
      • L / D = 18.7 turbulent
    • Cruise
      • C L = 0.54
      • L / D = 24.4
    • Transonic Drag Rise
      • M DD = 0.82
      • M crit = 0.71
    Alberti -
  • Parasite Drag Buildup Alberti -
    • C D = 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 - 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
    Alberti -
  • 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 - Hackmod.com
  • Ground Integration Alberti -
  • Questions? Alberti -