AAE 451 System Design Review March 30, 2010 Team 1 Alex Mondal Beth Grilliot Brien Piersol Heath Cheung Jason Liu Jeff Cohen Jeremy Wightman Kit Fransen Lauren Hansen Nick Walls Ryan Foley Tim Fechner 1 TABLE OF CONTENTS EXECUTIVE SUMMARY ....................................................................................................................................... 3 MISSION STATEMENT ......................................................................................................................................... 4 DESIGN MISSION ........................................................................................................................................................... 4 TYPICAL OPERATING MISSION .......................................................................................................................................... 5 MAJOR DESIGN REQUIREMENTS ........................................................................................................................ 5 AIRCRAFT CONCEPT SELECTION .......................................................................................................................... 6 ENGINEERING LOGIC ....................................................................................................................................................... 6 OUTCOME AND LAYOUTS .............................................................................................................................................. 10 COMPLIANCE MATRIX ................................................................................................................................................... 15 ADVANCED AND UNCONVENTIONAL TECHNOLOGIES UNDER CONSIDERATION ................................................. 16 CANARDS ................................................................................................................................................................... 17 FORWARD‐SWEPT WINGS ............................................................................................................................................. 18 BLENDED‐WING‐BODY ................................................................................................................................................. 19 PROPFAN ENGINES ....................................................................................................................................................... 21 LAMINAR FLOW CONTROL ............................................................................................................................................. 21 CONSTRAINT ANALYSIS AND DIAGRAMS ........................................................................................................... 23 BACK SWEPT WING AIRCRAFT CONCEPT .......................................................................................................................... 24 FORWARD SWEPT WING AIRCRAFT CONCEPT ...................................................................................................................... 25 BLENDED WING BODY AIRCRAFT CONCEPT ......................................................................................................................... 26 TRADE STUDIES ........................................................................................................................................................... 28 SIZING STUDIES ................................................................................................................................................. 30 CURRENT APPROACH .................................................................................................................................................... 30 DRAG PREDICTION ............................................................................................................................................... 35 ENGINE MODEL ........................................................................................................................................................... 35 ENGINE AND PROPULSION SELECTION ............................................................................................................... 37 APPROACH TO MODEL ENGINE ....................................................................................................................................... 44 STABILITY .......................................................................................................................................................... 45 INITIAL VERTICAL TAIL SIZING ........................................................................................................................................ 48 SUMMARY AND NEXT STEPS ............................................................................................................................. 50 WORKS CITED ................................................................................................................................................... 52 APPENDIX A: HOUSE OF QUALITY ...................................................................................................................... 55 APPENDIX B: MERIT POOL ................................................................................................................................. 56 2 EXECUTIVE SUMMARY From market research, Team 1 determined that a long range business jet, capable of a still‐air mission of 7100 nmi would be most marketable in the year 2020. To complete these requirements, Team 1 sketched over 20 aircraft designs and assessed them using engineering logic. Three designs were selected: a back swept, forward swept, and blended wing aircraft. We researched the unconventional technologies of canards, forward swept, and blended wing bodies, as well as propfans. From this research, canards demonstrated improved lift characteristics at the cost of difficult placement. Forward swept aircraft have improved lift characteristics, allowing for decreased takeoff and landing distances. However, their design also necessitates improved composite materials used in the wing. Blended wing bodies demonstrate increased lift performance. However, aesthetically it may be less desirable due to the lack of windows in the cabin. From the constructed sizing code, we found initial empty weights. For the back swept configuration, its empty weight was 95,000 lbs. The forward swept’s empty weight was 99,000 lbs, and the blended wing body’s was 88,000 lbs. With these determined weights, and estimates for the passengers, fuel, and engines, we calculated stability. We found all three designs to be stable. The back swept aircraft had a 5.1% static margin, the forward swept aircraft had a 13.4% static margin and the blended wing body aircraft had a 10.2% static margin. Overall, the designs demonstrated viability. Further sizing refinement will better quantify the performance of these designs. We will be integrating our component weight build up into the sizing code in order to create a better iterative process. Improving our drag code will also provide better analysis for the generated values. 3 MISSION STATEMENT To engineer a conceptual business aircraft solution capable of transporting esteemed passengers, in luxury, while adhering to NASA’s N+2 environmental goals. In order to abide by NASA’s N+2 environmental standards, our concept will provide reduced NOx emissions, reduced noise pollution, increased fuel efficiency, and an increased percentage of recyclable materials used in construction. These key topics will help address the primary concerns of environmentally conscious groups. DESIGN MISSION To reach our mission statement goals, the idea of a long‐range business aircraft was chosen. By looking at long‐range business aircraft currently in production and choosing attributes that we believe we can improve, we created the design mission summarized below. ‐ 12 – 19 Passengers + 4 Crew ‐ Cruise Altitude > 40,000 ft ‐ Cruise Speed 0.85 Mach ‐ Still‐air Range of 7,100 nmi ‐ Takeoff Field Length 4,700 – 5,000 ft ‐ Landing Field Length 2,500 – 3,000 ft A high operating ceiling has many benefits. By choosing a cruise altitude of greater than 40,000 feet, our business jet will operate above the majority of air traffic allowing for higher speeds and a cruise‐climb method, increasing altitude as the aircraft becomes lighter from burning fuel. This method improves the overall efficiency of the engines and decreases fuel usage. Timely flights are a desirable characteristic that consumers desire in a business jet. High cruise speed directly correlates to the flight duration. Therefore, we chose the cruise speed of 0.85 Mach from historical data as it offers a high speed while maintaining fuel efficiency. A range of 7,100 nmi, a conservative distance from Los Angeles to Hong Kong with a 60 kts headwind, was the design mission range for the aircraft. Destination flexibility is also important for a desirable business jet solution. With a takeoff field length of 4,700 – 5,200 feet and a landing field length of 2,500 – 3,000 feet, these aircrafts will have access to many small 4 airports; this reduces the aircraft design’s reliance on larger and more congested terminals and, thereby, improves turnaround time and decreases wait times. TYPICAL OPERATING MISSION It is not reasonable to expect the designed aircraft to operate at the full design mission at all times. Therefore, we designed the typical operating mission to carry 6 – 8 passengers, with 3 crew, over approximately