Fuselage self-propulsion by static-pressure thrust - CAFE Foundation

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potential 60% power saving for 2-seat aircraft and 40% 9. F. R. Goldschmied, "Proposal for the study of power for 4-seat aircraft, as to Application of Boundary-Layer Control to Lighter- than-air CFsft", Goodyear Aircraft Corp. Rpt. specific current designs. A similar study was GER-5796, 1954. presented by the same author (1986)35 for general aviation aircraft based on the McLemore (1962) body/wake-propeller configuration. Pressure thrust is the most efficient form of fuselage self-propulsion; it is based on the best 34 10. F. R. Goldschmied, 'A Theoretical Aerodynamic Analysis of a Boundary Layer Controlled Airship Bull", Goodyear Aircraft Corp. Rpt. GER-6251, 1954. 11. D. Kuchemann and J. Weber, wAerodynamics of Propulsion", McGraw Bill Book Co., 1953. possible implementation of the BLC system. It cannot be overemphesized that the most careful be 12. B. Edwards, "Laminar Flow Control-Concepts, Experiences, Speculations", AGARD Rpt. 654, given to thc optimization of this system for any given "Special Course on Concepts for Drag Reduction", aircraft design application. April 1977. Acknowledgements The contributions of Justin McCarthy and of Dennis Bushnell are gratefully acknowledged by the author. At the David W. Taylor Naval Ship R&D Center, McCarthy convinced the author that a new look was needed by pointing out, again and again, that the skin-friction drag was always there, acting on the body's wetted area, no matter what was done to the boundary-layer at the tail, At the NASA Langley Research Center, Bushnell was the first to suggest the pressure thrust concept for bodies and to hold many useful discussions with the author References 1. J. B. Edwards, 'Fundamental Aspects of Propulsion for Laminar Flow Aircraft". Boundary Laver and Flow Control, G. V. Lachmann, Ed.', Vdl. 11, Pergamon Press, 1961. 2. J. B. Fanucci, et al, "Navy V/STOL Aerodynamics: Final Report", West Virginia University, Aerospace Engrg. Rpt. TR-40, Feb. 1974. 3. 4. I. M. Davidson, 'Some Engineering Problems of the Jet Flap', Boundary Layer and Flow Control, G. V. Lachmann, Ed., Vol. I, Pergamon Press, 1961. N. A. Dimmock, "Some Further Jet Flap Experiments", ARC CP#345, 1957. 5. B. S. Stratford, "A Further Discussion on Mixing and the Jet Flap", Aeronautical Quarterly, Vol. VII, Aug. 1956. 6. B. S. Stratford, "Mixing and the Jet Flap", Aeronautical Quarterly, Vol. VII, May 1956. 7. E. Schlichting and E. Truckenbrodt, "Aerodynamics of the AirplaneM, McGraw Hill International Book Go. 1979 (Ch. 5). 8. P. A. Cerreta, 'Wind-Tunnel Investigation of the Drag of a Proposed Boundary-Layer Controlled Airship', David W. Taylor Model Basin, Aero Rpt. 914, 1957. ---' -19. 13. M. P. Earsche, F. A . Pake and A. R. Wasson, "An Investigation of a Boundary-Layer Controlled Airship", Goodyear Aircraft Corp. Rpt. GER-8399, 1957. 14. F. R. Goldschmied, "Integrated Bull Design, Boundary-Layer Control and Propulsion of Submerged Bodies", AIAA Paper 66-658, Second Propulsion Conference, Colorado Springs, CO, June 1966. AIAA J. Eydronautics Val. I #1, p. 2-11, 1967. 15. F. R. Goldschmied, "Aerodynamic Analysis of the 1969 Wind-Tunnel Tests of the Goldschmied Body. Vol. I - Slot Geometries and Body Pressure Distributions. Vol. I1 - Boundary-Layer Suction, Transition and Wake-Dragn, Westinghouse R&D Center, Report 77-1ES-BLCON-R1, RZ, 1977. 16. J. E. Preston, N. Gregory and A . G. Rawcliffe, "The Theoretical Estimation of Power Requirements far Slot-Suction Aerofoils, with Numerical Results for Two Thick Griffith Type Sections", British ARC R&M 2577, 2953. 17. F. R. Goldschmied, "ind-Tunnel Test of the Modified Goldschmied Model with Propulsion and Empennage: Analysis of Test Results", David W. Taylor Naval Ship R&D Center, Rpt. ASED-CR-02-86, 1986. 18. F. R. Goldschmied, "Integrated Hull Design, Boundary-Layer Control and Propulsion of Submerged Bodies: Wind-Tunnel Verification", AIAA Paper 82- 1204, AIAA/SAE/ASME Joint Propulsion Conference, June 1982 19. F. R. Goldschmied, "Jet Propulsion of Subsonic Bodies with Jet Total-Read Equal to Free- Stream's", AIAA Paper 83-1790, AIAA Applied Aerodynamics Conference, July 1983. 20. E. J. Howe and B. J. Neumann, n A Experimental ~ Evaluation of a Low Propulsive Power, Discrete Suction Concept Applied to an Axisymmetric Vehicle", David W. Taylor Naval Ship R&D Center TM 16-82/02, 1982. 21. F. R. Goldschmied, 'Wind-Tunnel Demonstration of an Optimized LTA System with 65% Power Reduction and Neutral Static Stability", AIM Paper 83.1981, LTA Systems Conference, July 1983. 22. F. R. Goldschmied, "On the Aerodynamic optimization of Mini-RPV and Small GA Aircraft", AIAA Paper 84-2163, Applied Aerodynamics Conference, August 1984.
23, E. J. Neumann, "Optimum Forebody Shaping for Axisymmetric Submersibles with Turbulent Boundary- Layers and BLC Afterbodies" David W. Taylor Naval Ship R&D Center DTNSRDC-83j055, 1983. 24 25. 26. 28. 29. 30. 31, 32 33, E. E. Freeman, nMeasurements of Flow in the Boundary-Layer of a 1/40-Scale Model of the U.S. Airship Akron', NACA Rpt. 430, 1932. 34, E. C. Mdemore, "Wind Tunnel Tests of a 1/20-Scale Airship Model with Stern Propellers', NASA TN D- 1026, Jan. 1962. 35, F. R. Goldschmied, RAeradynamic Design of Low- Speed Aircraft with a NASA Fuselage/Wake-Propeller Configuration", AIAA Paper 86-2693, Aircraft Systems, Design & Technology Meeting, Dayton, 08, October 1886. 36 37 B. J. Neumann, "Advanced Laminar Flow Forebody Shaping for Axisymmetric Submersibles with Boundary-Layer Control Afterbodies (U)", David W. Taylor Naval Ship R&D Center DTNSRDC-86/008, 1886. (Confidential). H. J. Hone, nPerformance Analysis of Modified Goldschmied Type Integrated Propulsion Systems for Axisymmetric Bodies" David W. Taylor Naval Ship R&D Center DTNSRDC-85jOO9, 1986. R. L. Walker, "An Inverse Method for Axisymmetric Bodies", David W. Taylor Naval Ship R&D Center ASED-SS/OZ, 1985. 27. 3. F. Slamski and D. C. McMillen. nDDevelooment of Laminar Flaw Axisymmetric Bodies with BLC Afterbodies for Bigh Reynolds Numbers (U)", David W. Taylor Naval Ship R&D Center DTNSRDC-86/018, 1986. ~ (Confidential) I. E. Abbott, "The Drag of Two Streamlined Bodies as Affected by Protuberances and Appendages", NACA Report 451, 1932. E. J. Holmes, "Letter to F. R. Goldschmied", Feb. 9, 1987. F. R. Goldschmied, "An Approach to Turbulent Incompressible Separation under Adverse pressure Gradients", AIM J. of Aircraft, Vol. 2, March- April 1965, pp. 108-115. F. R. Goldschmied, mAAerodynamiz Analysis of the 1970 Wind-tunnel Tests of a Laminar-Forebody Tailboam Body, With and Without Turbulent Separationn, Westinghouse R&D Center Report 72- lE9-BLCON-R1, March 1972. J. S. Murphy, "The Separation of Axially Symmetric Turbulent Boundary-Layersn, Douglas Aircraft Co. Rpt. ES 17513, March 1954. W. Pfenninger, "Laminar Flow Control, Laminarisation', AGARD Report No. 654, wSpecial Course on Concepts for Drag Reduction", 1977, pp. 3-1 - 3-75. A. Y. 0. Smith, T. R. Stokes, Jr. and R. L. Lee, nOptimum Tail Shapes for Bodies of Revolutionn, AIM J. Eydronautics, Vol. 15, No. 1-4, January- December 1981, pp 67-73. -20- L; W
Page 1 and 2: AI AA-87-2935 Fuselage Self-Propuls
Page 3 and 4: I. Introduction This paper attempts
Page 5 and 6: ~ To simplify the problem it is ass
Page 7 and 8: the slot's leading edge: the minimu
Page 9 and 10: Fig. 9 - Photo of Wind-Tunnel Insta
Page 11 and 12: 0,010 (transition at 65% length, se
Page 13 and 14: " a. L Y w 0 2 1 .0 0.8 0.6 0.4 " 0
Page 15 and 16: Y r rn 1 .o 0.0 0.4 UliPROPiLLiD Al
Page 17 and 18: 0.987; the static-pressure Coeffici
Page 19: Configuration Integrated Conf. 00 I

Fuselage self-propulsion by static-pressure thrust - CAFE Foundation

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