System Definition Review AAE 451 Team Gold Jet

System Definition Review AAE 451 Team Gold. Jet Andrew Mizener Diane Barney Jon Coughlin Jared Scheid Mark Glover Michael Coffey Donald Barrett Eric Smith Kevin Lincoln

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

1 x 1 Seating Layout • 1 x 1 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

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

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

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

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

2 x 2 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 2 g Manuever, • 250 kts , 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 = 0. 678 (ρ ratio) CD 0 = 0. 018 AR = 2 ΛLE = 45° dmax = 11. 75 ft l = 180 ft CDw = 0. 00644 • Subsonic Maneuver – – CD 0 & AR e = 0. 7 • Takeoff – – β=1 CL, max, TO = 1. 2 Field Length = 10000 ft s. TO = 6000 ft • Landing – – – αrev = 0. 2 β=1 CL, max, Land= 1. 5 μ = 0. 2 (wet concrete/asphalt) Field Length = 10000 ft s. Land = 6000 ft • 2 nd Segment Climb – – CD 0, AR, ΛLE Four Engines (3% CGR) CL, max, TO = 1. 2 e. TO = 0. 525

Constraint Diagram Gold. Jet Constraint Diagram 1 0. 8 TSL/W 0 0. 6 Steady, Level Flight (1 g), M = 1. 8 @ h = 45 K ft 0. 4 Subsonic 2 g Manuever, 250 kts @ h =10 K ft Takeoff Ground Roll 6000 ft @ h = 1 K ft, +15° Hot Day 0. 2 Landing Ground Roll 6000 ft @ h = 1 K ft, +15° Hot Day 0 50 60 70 80 90 100 -0. 2 -0. 4 W/S [lb/ft 2] 110 120 130 140 150 Second Segment Climb Gradient Above h = 1 K ft, +15° Hot Day Landing Ground Roll 6000 ft @ h = 1 K ft, +15° Hot Day, No TR

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: 0. 375 Maximum Mach Number: 2 Cruise Mach Number: 1. 8 SFC: 0. 8 /hr • Resulting Weights – W 0=341, 000 lbs – We=126, 000 lbs – Wf =206, 000 lbs • Wing Area – S=2, 700 ft 2

Sonic Boom Prediction • Based upon Carlson – “Simplified Sonic-Boom Prediction” • Uses a series of nonlinear 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: 0. 155 seconds

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

Joined Wing Configuration • Joined Wing Planform • Canards • Engines podded and aft on fuselage • Circular Fuselage • Tricycle Landing Gear • 1 x 1 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?