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as suggested by NASA’s SFW N+3 goals. Descriptions of the vehicle, the superconducting system, and the propulsion system were presented with some zeroth-order weight and efficiency comparisons to the multiple turbofan system. Preliminary analysis suggests that fuel savings may be greater than 6 percent for a turboelectric propulsion system compared to distributed discrete turbofans. Beyond fuel savings, however, turboelectric propulsion systems introduce a very high degree of aircraft design and operational flexibility as a result of decoupling power production from power consumption. Lightweight superconducting generators, motors and power cables allow a small number of large turbo- 109. generators to power an arbitrary number of propulsor units. Either can be placed practically anywhere and in various orientations on the vehicle. This flexibility opens up design possibilities not obtainable with discrete turbofans or with distributed propulsion systems that employ mechanical power distribution by gearboxes and shafts. VI. Acknowledgments The authors would like to acknowledge Ronald Kawai and Sean Wakayama at Boeing Technology/Phantom Works, and James Stone and Eugene Krejsa at Diversitech, Inc., for their contribution to the earlier cruise-efficient short take-off and landing (CESTOL) vehicle analysis. We are also appreciative for the helpful interaction with Albert Kascak and Jeffrey Berton at NASA Glenn Research Center, and Andrew Hahn at NASA Langley Research Center for providing comments on turboelectric CESTOL vehicle concepts. Finally, a special thanks goes to Fayette Collier, NASA’s Subsonic Fixed Wing project principal investigator at Langley Research Center, for his support on current CESTOL activity. References 1. JPDO, “Making the NextGen Vision a Reality 2006 Progress Report to the Next Generation Air Transportation System Integrated Plan,” Joint Planning and Development Office, December, 2006. 2. Greener by Design, “Air Travel—Greener by Design,” Feb. 2002. 3. Kim, H.D., Berton, J.J., and Jones, S.M., “Low Noise Cruise Efficient Short Take-Off and Landing Transport Vehicle Study,” AIAA–2006–7738, Sept. 2006. 4. Stone, J.R., Krejsa, E.A., Berton, J.J. and Kim, H.D., “Initial Noise Assessment of an Embedded-Wing- Propulsion Concept Vehicle,” AIAA–2006–4979, July, 2006. 5. Hileman, J.I., Spakovszky, Z.S., Drela, M., Sargeant, M.A., “Airframe Design for Silent Aircraft,” AIAA Paper 2007–453, Jan. 2007. 6. de la Rosa Blanca, E., Hall, C.A., and Crichton, D., “Challenges in the Silent Aircraft Engine Design,” AIAA Paper 2007–454, Jan. 2007. 10. Küchemann, D., and Weber, J., Aerodynamics of Propulsion, New York: McGrawHill, 1953. 11. Smith Jr., L.H., “Wake Ingestion Propulsion Benefit,” Journal of Propulsion and Power, Vol. 9, No. 1, Jan-Feb. 1993. 12. Spence, D.A., “The Lift Coefficient of a Thin, Jet- Flapped Wing,” Proceedings of the Royal Society of London. Series A, Mathematical and Physical Sciences, Vol. 238, No. 1212, pp. 46–68, Dec. 1956. 13. Williams, J., Butler, S.F., and Wood, M.N., “The Aerodynamics of Jet Flaps,” Aeronautical Research Council Reports and Memoranda No. 3304, Jan. 1961. 14. Daggett, D., Hadaller, O., Hendricks, R., and Walther, R., “Alternative Fuels and Their Potential Impact on Aviation,” NASA/TM—2006-214365, Oct. 2006. 15. Guynn, M.D., Freeh, J.E., and Olson, E.D., “Evaluation of a Hydrogen Fuel Cell Powered Blended-Wing-Body Aircraft Concept for Reduced Noise and Emissions,” NASA/TM—2004-212989, Feb. 2004. 16. Kawai, R., “Quiet Cruise Efficient Short Take-Off and Landing Subsonic Transport System,” NASA/CR—2008- 215141, Apr. 2008. 17. Stone, J,R. and Krejsa, E.A., “Initial Noise Assessment of an Embedded-Wing-Propulsion Concept Vehicle, Final Report,” NASA/CR—2008-215140, Apr. 2008. 18. Wakayama, S. and Kroo, L., “Subsonic Wing Planform Design Using Multidisciplinary Optimization,” Journal of Aircraft, Vol. 32, No. 4, Jul.–Aug. 1995, pp. 746–753. 19. Bushnell, D. M., “Frontiers of the ‘Responsibly Imaginable’ in (Civilian) Aeronautics,” AIAA Paper 98– 0001, 1998. 20. Grasmeyer, J.M., et al., “Multidisciplinary Design Optimization of a Strut-Braced Wing Aircraft With Tip- Mounted Engines,” MAD–98–01–01, Virginia Polytechnic Institute and State University, Jan. 1998. 21. Brown, G.V., Kascak, A. F., Ebihara, B., Johnson, D., Choi, B., Siebert, M., and Buccieri, C., “NASA Glenn Research Center Program in High Power Density Motors for Aeropropulsion,” NASA/TM—2005-213800, 2005. 22. Kalsi, S.S, Weeber, K., Takesue, H., Lewis, C., Neumueller, H.W., and Blaugher, R.D., “Development Status of Rotating Machines Employing Superconducting Field Windings,” Proc. IEEE, vol. 92, no. 10, Oct. 2004, pp. 1688–1704. 7. Kim, H.D. and Saunders, J.D, “Embedded Wing Propulsion Conceptual Study,” NATO RTA Symposium on Vehicle Propulsion Integration, RTO–MP–AVT–100, Oct. 2003. 8. Ko, A, Leifsson, L.T., Schetz, J.A., Mason, W.H., and Haftka, R.T., “MDO of a Blended-Wing-Body Transport Aircraft with Distributed Propulsion,” AIAA–2003–6732, Nov. 2003. 9. Smith, A.M.O. and Roberts, H.E., “The Jet Airplane Utilizing Boundary Layer Air for Propulsion,” Journal of the Aeronautical Sciences, Vol. 14, No. 2, 1947, pp. 97– 10PDF Image | Distributed TurboElectric Propulsion for Hybrid Wing Aircraft
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