NASA/CR—2010-216794/VOL1 N+3 Aircraft Concept Designs and Trade Studies, Final Report Volume 1 E.M. Greitzer, P.A. Bonnefoy, E. De la Rosa Blanco, C.S. Dorbian, M. Drela, D.K. Hall, R.J. Hansman, J.I. Hileman, R.H. Liebeck, J. Lovegren, P. Mody, J.A. Pertuze, S. Sato, Z.S. Spakovszky, and C.S. Tan Massachusetts Institute of Technology, Cambridge, Massachusetts J.S. Hollman, J.E. Duda, N. Fitzgerald, J. Houghton, J.L. Kerrebrock, G.F. Kiwada, D. Kordonowy, J.C. Parrish, J. Tylko, and E.A. Wen Aurora Flight Sciences, Cambridge, Massachusetts W.K. Lord Pratt & Whitney, East Hartford, Connecticut December 2010 NASA STI Program . in Profi le Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. 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Lovegren, P. Mody, J.A. Pertuze, S. Sato, Z.S. Spakovszky, and C.S. Tan Massachusetts Institute of Technology, Cambridge, Massachusetts J.S. Hollman, J.E. Duda, N. Fitzgerald, J. Houghton, J.L. Kerrebrock, G.F. Kiwada, D. Kordonowy, J.C. Parrish, J. Tylko, and E.A. Wen Aurora Flight Sciences, Cambridge, Massachusetts W.K. Lord Pratt & Whitney, East Hartford, Connecticut Prepared under Cooperative Agreement NNX08AW63A National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 December 2010 Acknowledgments Financial support for this project was provided by NASA under Cooperative Agreement Number NNX08AW63A. This support is gratefully acknowledged. We would also like to thank G. Brown, J. Felder, H-D Kim, K. Pham, and A. Strazisar of NASA Glenn Research Center (GRC) for their interest and help. We also would like to acknowledge the help of P.J. Masson from Magnetolab for his technical advisement. Team Participants: The following have contributed to the work described in this report. Their affi liation is shown by this Key: + Aurora Flight Sciences, @ Boeing (ret.), # MIT, * Pratt&Whitney, and ‡ Imperial College. Holly Anderson# Robert Bengtson* Phillip Bonnefoy# Nicholas Cumpsty‡ Elena De la Rosa Blanco# Mark Drela# Christopher Dorbian# Jessica Duda+ Alan Epstein* Nathan Fitzgerald+ Lindley Graham+ Edward Greitzer# David Hall# John Hansman# Karl Hasel* James Hileman# Jeremy Hollman+ James Houghton+ Jack Kerrebrock+ James L. Kirtley# George Kiwada+ Rob Kline* Atul Kohli* David Kordonowy+ Steve Kramer* John Langford+ Robert Liebeck# Wesley Lord* Jonathan Lovegren# Justin McClellan+ Siamak Masoudi* Randy McKinney* Brent McLaughlin+ Pritesh Mody# Bruce Morin* Diana Park# Joe Parrish+ Julio Pertuze# Sho Sato# Zolti Spakovszky# Brent Staubach* Jayant Sabnis* Gabe Suciu* Choon Tan# John Tylko+ Ian Waitz# Ed Wen+ Gerald Wilson# Robert Woodling@ Adam Woodworth+ This report contains preliminary fi ndings, subject to revision as analysis proceeds. This work was sponsored by the Fundamental Aeronautics Program at the NASA Glenn Research Center. Level of Review: This material has been technically reviewed by NASA technical management. Available from NASA Center for Aerospace Information National Technical Information Service 7115 Standard Drive 5301 Shawnee Road Hanover, MD 21076–1320 Alexandria, VA 22312 Available electronically at http://gltrs.grc.nasa.gov Program Abstract MIT, Aerodyne Research, Aurora Flight Sciences, and Pratt & Whitney have collaborated to address NASA’s desire to pursue revolutionary conceptual designs for a subsonic commercial transport that could enter service in the 2035 timeframe. The MIT team brings together multidisciplinary expertise and cutting-edge technologies to determine, in a rigorous and objective manner, the potential for improvements in noise, emissions and performance for subsonic fixed wing transport aircraft. The collaboration incorporates assessment of the trade space in aerodynamics, propulsion, operations, and structures to ensure that the full spectrum of improvements is identified. Although the analysis focuses on these key areas, the team has taken a system-level approach to find the integrated solutions that offer the best balance in performance enhancements. Based on the trade space analyses and system-level assessment, two aircraft have been identified and carried through conceptual design to show both the in- depth engineering that underpins the benefits envisioned and also the technology paths that need to be followed to enable, within the next 25 years, the development of aircraft three generations ahead in capabilities from those flying today. NASA/CR—2010-216794/VOL1 iii Table of Contents 1 Executive Summary ..................................................................................................................................... 1 1.1 Configuration Definition ............................................................................................................................. 5 2 Scenario ...................................................................................................................................................... 6 2.1 Introduction ............................................................................................................................................... 6 2.2 Method ...................................................................................................................................................... 6 2.3 Scenario Dimensions ................................................................................................................................. 7 2.4 Requirements ............................................................................................................................................ 25 3 Figures of Merit ........................................................................................................................................... 31 3.1 NASA N+3 Metrics ...................................................................................................................................... 31 3.2 Climate ....................................................................................................................................................... 41 4 Program Approach ...................................................................................................................................... 45 4.1 Overall Process .......................................................................................................................................... 45 4.2 Rationale for Examination of Two Different Aircraft Configurations ........................................................ 46 5 D8 “Double-Bubble” Design Concept ........................................................................................................... 48 5.1 Design Overview ........................................................................................................................................ 48 5.2 Design Concept and Technologies .............................................................................................................