System Definition Review AAE 451 Andrew Mizener Diane Barney Jon Coughlin Jared ScheidMark Glover Michael CoffeyDonald Barrett Eric SmithKevin Lincoln Team GoldJet

Mission Statement To design a profitable, supersonic aircraft capable of Trans-Pacific travel to meet the needs of airlines and their passengers around the world.

Major Design Requirements Trans-Pacific Range: − Longer range increases available routes High Cruise Speed : −Makes shorter trip times and allows for more legs per day Good Cruise Efficiency: –Lowers the cost of fuel and the max gross weight

Design Mission Los Angeles (LAX) – Shanghai (PDG) –Range: 5,650 nautical miles

Morphological Matrix To assist Pugh’s Method and Concept Selection Listed design categories and all options

First Concepts Four Concepts Chosen, along with Datum Showed immediate narrowing of possible ideas in some categories –Two wing planforms –Two fuselage types –One landing gear style

Pugh’s Method Two rounds –First against the Datum –Second against one of our first designs (Concept 2) Second round shown –Some narrowing of categories as process went along

Condensed Concepts Taking results of Pugh’s Method, two concepts emerged for further study –One based around a Double-Delta wing Result of min/maxing DD concepts Three Design Choices to make –Engine Location, Canards, and Tail Configuration –One based around a Joined Wing

1x1 Seating Layout 1x1 Seating Configuration Design allows for long slender body, reducing drag Carry-on baggage stowed next to passenger –Allows for easier in flight access –Up to two carry-on bags can be carried due to increased space

1x1 Top View Length 90 feet Lavatories positioned at the front and rear of the cabin Galley located forward Lav Galley Entry Door

1x1 Cross-Section Diameter: 10 ft Aisle Width: 26 inches Aisle Height: 76 inches Seat Pitch: 40 inches Carry On Storage

2x2 Seating Layout 2x2 Seating Configuration Shorter fuselage length, enabling more radical Sears- Haack shaping Carry-on baggage stored overhead

2x2 Top View Length 54 feet Lavatories located aft Galley located aft Lav Galley Entry Door

2x2 Cross-Section Diameter: 11 feet 8 inches Aisle Width: 26 inches Aisle Height: 76 inches Seat Pitch: 40 inches

Performance Constraints 5 main performance constraints identified: –Steady, Level Flight M = 1.8, h = 45,000 ft –Subsonic 2g Manuever, 250kts, h = 10,000 ft –Takeoff Ground Roll 5400 ft, h = 1,000 ft, +15° Hot Day –Landing Ground Roll 5400 ft, h = 1,000 ft, +15° Hot Day –3% Second Segment Climb Gradient (4 engines) Above h = 1,000 ft, +15° Hot Day

Constraint Assumptions Cruise –Lapse Rate = (ρ ratio) –C D0 = –AR = 2 –Λ LE = 45° –d max = ft –l = 180 ft –C Dw = Subsonic Maneuver –C D0 & AR –e = 0.7 Takeoff –β = 1 –C L,max,TO = 1.2 –Field Length = ft –s TO = 6000 ft Landing –α rev = 0.2 –β = 1 –C L,max,Land = 1.5 –μ = 0.2 (wet concrete/asphalt) –Field Length = ft –s Land = 6000 ft 2 nd Segment Climb –C D0, AR, Λ LE –Four Engines (3% CGR) –C L,max,TO = 1.2 –e TO = 0.525

Constraint Diagram

Current Sizing Method Based upon calculating the fuel fraction as described in Raymer Empty weight fraction based upon historical aircraft data Technical Factor of 0.95 for advanced materials

Results Design Variables – Mission Range: 5650 nmi – Aspect Ratio: 2 – Wing Loading: 125 lb/ft 2 – Thrust to Weight: – Maximum Mach Number: 2 – Cruise Mach Number: 1.8 – SFC: 0.8 /hr Resulting Weights – W 0 =341,000 lbs – W e =126,000 lbs – W f =206,000 lbs Wing Area – S=2,700 ft 2

Sonic Boom Prediction Based upon Carlson –“Simplified Sonic-Boom Prediction” Uses a series of non- linear factors based on altitude and shape Determines –Overpressure –Duration

Baseline Overpressure Cruise Condition –M=1.8 –Alt = 45,000 ft Results –Overpressure: 1.66 lb/ft 2 –Duration: seconds

Double Delta Configuration Double Delta Wing Planform Raked Wingtips Low wing Blended Wing/ Circular Fuselage Tricycle Landing Gear 2x2 Cabin Canard, Tail, Engine Location to be optimized DD with no canards and Conventional Tail Rough DD with Canards and No Tail

Joined Wing Configuration Joined Wing Planform Canards Engines podded and aft on fuselage Circular Fuselage Tricycle Landing Gear 1x1 Cabin

Next Steps Preliminary analysis Main concept selection Detailed analysis Final layout/configuration selection

Concept Analysis Double Delta –Engine placement Drag effects Ground clearance –Maintenance cost –Landing gear size/weight Noise shielding –Canards vs. horizontal tail Drag varying with surface size Canard issues at take-off Airport compatibility –Fuselage/wing blending Joined Wing –Wing structure Complexity Fuel storage Weight savings Aerodynamic performance

Analysis Topics Aerodynamics –Cross-sectional area plot –Wave drag –Induced drag –Boom forming Structures –Strength analysis –Weight and weight distribution Propulsion –Engine model –Engine choice Cost Model Systems –Airport gate compatibility –Ground clearance Control –Stability –Static Margin –CG travel Optimization –Detailed sizing –Carpet plots

Questions?