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

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

“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  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

Design Mission 2 – Short Range Round Trip 5

Design Mission 3 – Regional Short Hops 6

 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

 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

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

Concepts for second iteration 10 Aircraft Concept Selection

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 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

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

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

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 NASA TRL - Tandem Wings - Variable Sweep - Unducted Fan - Composites Overall Aircraft 3 9

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

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

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

New manufacturing processes Overall Weight savings Material Composition by Weight 19

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

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

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

Recent Sizing Studies Sizing Approach Basic Assumptions for L/D, We/Wo, SFC, noise - Matlab Scripts, Quicksizing - Windtunnel data (Javafoil ©) - Oswald Efficiency factor = 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

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

Compliance Matrix 25 TargetThresholdCurrent Runway Length (ft)< 2000< 3000 max payload (nmi) M CRUISE Ramp weight (lbs) Price (M $)4045- Passengers

- 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

Questions and Comments THANK YOU FOR YOUR TIME