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Design of a morphing flap in a two component airfoil with a droop nose

  • Carozza, Antonio (Dipartimento di Meccanica dei Fluidi, Centro Italiano Ricerche Aerospaziali, CIRA)
  • 투고 : 2016.01.06
  • 심사 : 2016.05.27
  • 발행 : 2017.01.25

초록

The performances of lifting surfaces are particularly critical in specific flight conditions like takeoff and landing. Different systems can be used to increase the lift and drag coefficients in such conditions like slat, flap or ailerons. Nevertheless they increase the losses and make difficult the mechanical design of wing structures. Morphing surfaces are a compromise between a right increase in lift and a reduction of parts movements involved in the actuation. Furthermore these systems are suitable for more than one flight condition with low inertia problems. So, flap and slats can be easily substituted by the corresponding morphing shapes. This paper deals with a genetic optimization of an airfoil with morphing flap with an already optimized nose. Indeed, two different codes are used to solve the equations, a finite volume code suitable for structured grids named ZEN and the EulerBoundary Layer Drela's code MSES. First a number of different preliminary design tests were done considering a specific set of design variables in order to restrict the design region. Then a RANS optimization with a single design point related to the take-off flight condition has been carried out in order to refine the previous design. Results are shown using the characteristic curves of the best and of the baseline reported to outline the computed performances enhancements. They reveal how the contemporary use of a morphing acting on the nose of the main component and the trailing edge of the flap drive towards a total not negligible increment in lift.

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참고문헌

  1. Amato, M. and Catalano, P. (2000), "Non Linear ${\kappa}-{\varepsilon}$ turbulence modeling for industrial applications", ICAS 2000 Congress, Harrogate, UK.
  2. Amato, M., Paparone, L., Catalano, P. and Puoti, V. (1999), "Zen flow solver, Zonal Euler Navier-stokes flow solver user guide", Technical Report, CIRA, Centro Italiano Ricerche Aerospaziali.
  3. Anderson, J.D. Jr (2011), Fundamentals of aerodynamics. McGraw-Hill Higher Education, 3rd edition.
  4. Barbarino, S., Bilgen, O., Ajaj, R.M., Friswell, M.I. and Inman, D.J. (2011), "A review of morphing aircraft", J. Intell. Mater. Syst. Struct., 22, 823-877. https://doi.org/10.1177/1045389X11414084
  5. Catalano, P. and Amato, M. (2001), "Assessment of ${\kappa}-{\omega}$ turbulence modeling in the CIRA flow solver ZEN", ECCOMAS 2001 Conference, Swansea, Wales.
  6. Ferziger, J. H. and Peric, M. (1996), Computational Methods for Fluid Dynamics, Springer-Verlag, Berlin & Heidelberg.
  7. Jameson, A. (1991), "Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings", AIAA Paper, AIAA 10th Computational Fluid Dynamics Conference, Honolulu, HI, June.
  8. Kok, J. (2000), "Resolving the dependence on free-stream values for the ${\kappa}-{\omega}$ turbulence model", AIAA J., 38(7), 1292-1295. https://doi.org/10.2514/2.1101
  9. Kuhn, T. (2010), "Aerodynamic optimization of a two-dimensional two-element high lift airfoil with a smart droop nose device", 1st EASN Association Workshop on Aerostructures, Paris, France
  10. Mark, D. (2007), A User's Guide to MSES 3.05, MIT Department of Aeronautics and Astronautics, July.
  11. Marongiu, C., Catalano, P., Amato, M. and Iaccarino, G. (2004), "U-ZEN: a computational tool solving U-RANS equations for industrial unsteady applications", 34th AIAA Fluid Dynamics Conference, Portland (Or), AIAA Paper 2004-2345.
  12. Olympio, K.R. and Gandhi, F. (2010a), "Flexible skins for morphing aircraft using cellular honeycomb cores", J. Intel. Mater. Syst. Struct., 21, 1719-1735. https://doi.org/10.1177/1045389X09350331
  13. Olympio, K.R. and Gandhi, F. (2010b), "Zero poisson's ratio cellular honeycombs for flex skins undergoing one-dimensional morphing", J. Intel. Mater. Syst. Struct., 21, 1737-1753. https://doi.org/10.1177/1045389X09355664
  14. Quagliarella, D. (2003), "Airfoil design using Navier-Stokes equations and an asymmetric multi-objective genetic algorithm", Evolutionary Methods for Design, Optimization and Control Applications to Industrial and Societal Problems, International Center for Numerical Methods in Engineering (CIMNE), Barcelona, Spain.
  15. Secanell, M., Suleman, A. and Gamboa, P. (2006), "Design of a morphing airfoil using aerodynamic shape optimization", AIAA J., 44(7), 1550-1562. https://doi.org/10.2514/1.18109
  16. Shili, L., Wenjie, G. and Shujun, L. (2008), "Optimal design of compliant trailing edge for shape changing", Chin. J. Aeronaut., 21, 187-192. https://doi.org/10.1016/S1000-9361(08)60024-2
  17. Thill, C., Etches, J., Bond, I., Potter, K. and Weaver, P. (2008), "Morphing skins", Aeronaut. J., 112, 117-139. https://doi.org/10.1017/S0001924000002062
  18. Vicini, A. and Quagliarella, D. (1997), "Inverse and direct airfoil design using a multi-objective genetic algorithm", AIAA J., 35(9), 1499-1505. https://doi.org/10.2514/2.274
  19. Wilcox, D.C. (1994), Turbulence Modeling for CFD, DCW Industries Inc., La Canada, Los Angeles, California.

피인용 문헌

  1. New Concept for Aircraft Morphing Wing Skin: Design, Modeling, and Analysis vol.57, pp.5, 2017, https://doi.org/10.2514/1.j058102
  2. Design Criteria for Variable Camber Compliant Wing Aircraft Morphing Wing Skin vol.58, pp.2, 2020, https://doi.org/10.2514/1.j058002