1. SYSTEMS DEFINITION REVIEW Brian Acker Lance Henricks Matthew Kayser Kevin Lobo Robert Paladino Ruan Trouw Dennis Wilde

2. System Definition Review Outline - MISSION STATEMENT - USE-CASE SCENARIOS - DESIGN REQUIREMENTS - CONCEPT SELECTION - ADVANCED TECHNOLOGIES - INITIAL CABIN LAYOUT - CONSTRAINT ANALYSIS - RECENT SIZING STUDIES 2

3. “Using innovative solutions to design a short-medium range aircraft that is efficient, eco-friendly, cost effective and capable of ESTOL, along with new technology to increase passenger traffic.” 3 Mission Statement  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES

4. 4  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES Design Mission 1 – Medium Range One Way

5. Design Mission 2 – Short Range Round Trip 5

6. Design Mission 3 – Regional Short Hops 6

7.  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES Design Requirements - ESTOL - Utilize Secondary Airports - Short to Medium Range - Safety / Reliability - Passenger Comfort - Low Overall Cost 7

8.  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES Aircraft Concept Selection Concepts for First Iteration of Pugh’s Method 1 2 4 5 6 7 8 9 3 8

9. 9 Aircraft Concept Selection Concept Descriptions for First Iteration of Pugh’s Method - (1) 2-deck biplane, swept wings, engines atop top wing, wings thru fuselage - (2) 2-deck biplane, swept wings, engines below bottom wing, top wing raised above fuselage - (3) Lifting body/ blended wing body, swing wing, t-tail - (4) Flying airfoil fuselage biplane, engines atop top wing - (5) Lifting body/ blended wing body, swing wing, no tail - (6) Standard tube with wings - (7) Tilt-Jet concept (similar to V-22), tube with wings - (8) Tube, forward-swept wings in rear, canards in front - (9) 2-fuselage biplane, wings mounted between fuselages, smaller wings outside fuselages, engines atop top wing

10. 1 2 3 4 5 6 7 Concepts for second iteration 10 Aircraft Concept Selection

11. Concept Descriptions for Second Iteration of Pugh’s Method 11 - (1) Flying airfoil fuselage biplane, wings collapse to form one large engine - (2) 2-deck biplane, swing wings, engines atop top wing (swivel), wings through fuselage - (3) 2-deck biplane, swing wings, engines below lower wing (swivel), top wing raised above fuselage - (4) Tandem-wing tube, swing wings, no horizontal stabilizer - (5) Biplane, forward-swept wings, engines below lower wing - (6) Biplane, forward-swept top wing, aft-swept lower wing, engines above top wing - (7) Lifting body/ blended wing body, swing wing, no tail

12. 12 Pugh’s Method Iteration 1 Best concepts: 5,4,6,1 Eliminated: 7,9,6 (too conventional) *New concepts to be added to next iteration using best of these concepts

13. Pugh’s Method 13 Best concepts: 4,1 Concept chosen: 4 (Tandem-wing tube, swing wings, no horiz. stabilizer) Iteration 2

14. Representative layout and three-view Isometric View 14 Side View Front View Top/Layout View

15. 15  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES Advanced Technologies Designing to meet requirements 2008 2038 NASA TRL - Tandem Wings - Variable Sweep - Unducted Fan - Composites 9 9 7 9 9 9 Overall Aircraft 3 9

16. Advantages – More lift and control at lower speeds – Large drag reduction in cruise – Reduction in T/O and Landing speeds and distance Disadvantages – Heavier – Shifts Center of Gravity backward (instability) – Increased Maintenance Advanced Technologies Variable Sweep 16

17. Segmented Variable Sweep Wing already patented Sweep a portion of the wing Preliminary estimates of 23 degree sweep (10-33) most beneficial Historic Estimates adds 4% to empty weight New technology and materials very possible Old swing wings developed with slide rule Advanced Technologies Variable Sweep/Incidence Use for possible stability correction Past usage to increase AoA and CL Heavy complex components 17

18. Composites – High Strength/Low Density – Carbon nanotube reinforced bike Titanium – New Processes of production – Powdered Titanium Development Material Selection 18

19. New manufacturing processes Overall Weight savings Material Composition by Weight 19

20. Propfan / Unducted Fan – 30% reduction in fuel consumption in 1980 with theory of 35% – Capable of M=.75 – 14,000 hp / 10,350Kw – High Cabin Noise – Danger of blade severance – Not practical for current layout Engine Advancement – 747 engines 1 st to 2 nd Generation – GeNx engine – Alternative Fuel – Renewable Power Advanced Technologies 20

21. Initial Cabin Layout  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES Seating arrangement Fuselage length / width / diameter 21 - Cabin Length: 70ft - Cabin Diameter: 10.75ft - Overall Length: 115ft - Single Aisle, 126 Passengers - Combination First and Economy classes - First Class: 3 rows, 4 seats per row - Economy: 19 rows, 6 seats per row

22. Constraint Analysis  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES Major performance constraints - Take off and land in < 3,000 ft - Carry 35,000 lb payload - Range of 1,000 nmi 22

23. Recent Sizing Studies Sizing Approach Basic Assumptions for L/D, We/Wo, SFC, noise - Matlab Scripts, Quicksizing - Windtunnel data (Javafoil ©) - Oswald Efficiency factor = 0.8 - Aspect Ratio = 9.5  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES 23

24. Recent Sizing Studies  OUTLINE  MISSION STATEMENT  USE-CASE SCENARIOS  DESIGN REQUIREMENTS  CONCEPT SELECTION  ADVANCED TECHNOLOGIES  INITIAL CABIN LAYOUT  CONSTRAINT ANALYSIS  RECENT SIZING STUDIES 126 Passengers @ 220 lb/pax Crew – 5 Operating empty weight (We) – 67,119 lbs Gross takeoff weight (Wo) – 117,262 lbs Empty weight fraction – 0.572 Fuel Fraction – 0.185 SFC – 0.85 1/hr AR – 9.5 Wing Sweep – 25° Vcruise – 461 kts M @ 35,000 ft – 0.80 CLmax = 0.949 L/D – 17.973 T/W – 0.43 (w/o high lift devices) Wing Loading (W/S) – 83.75 Range – 1,103 nmi 24

25. Compliance Matrix 25 TargetThresholdCurrent Runway Length (ft)< 2000< 3000 Range @ max payload (nmi)10008001103 M CRUISE 0.820.780.8 Ramp weight (lbs)--118000 Price (M $)4045- Passengers125150126

26. - Conceptual Design Review - Biot-Savart Lifting line theory - Basic Structural Analysis - Weight and Balance - Dynamic & Stability Testing Further Trade Studies - Supercritical Airfoils - Engine Types / Fuel Types - Variable incidence weight vs. benefit cost and added weight Next Steps 26

27. Questions and Comments THANK YOU FOR YOUR TIME