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Aerodynamic Analysis of Morphing Winglets for Improved Commercial Aircraft Performance

Yıl 2020, , 31 - 44, 24.06.2020
https://doi.org/10.30518/jav.716194

Öz

This article describes the performance benefits of variable winglet configurations. The primary variables investigated involved varying the winglet twist and dihedral angle of a comparable Airbus A330-300 wing structure. Numerical studies have been carried out in AVL (Athena Vortex Lattice Method). In order to illustrate the aerodynamic benefits of morphing winglet concepts for different flight regimes, values of twist (-10°< θ <10°, in steps of ±2.5°) and values of dihedral (-90°< θ <90°, in steps of ±15°) were designed and numerically investigated. The results obtained from this work indicate that by carefully adjusting morphing winglets on air vehicles (Airbus A330-300), the aerodynamic performance benefits could be achieved.

Kaynakça

  • [1] A. R. et al McGowan, “Recent Results from NASA’s Morphing Project,” in 9th International Symposium on Smart Structure and Materials, 2002, p. SPIE PaperNo.4698-11. [2] T. a. Weisshaar, “Morphing Aircraft Systems: Historical Perspectives and Future Challenges,” J. Aircr., vol. 50, no. 2, pp. 337–353, 2013. [3] D. McRuer and D. Graham, “Flight Control Century: Triumphs of the Systems Approach,” J. Guid. Control. Dyn., vol. 27, no. 2, pp. 161–173, 2004. [4] E. Wilson, “Nature photography,” Nature, vol. 82, no. 2100, pp. 371–372, 1910. [5] NASA, “21st Century Aerospace Vehicle, Morphing Airplane.” . [6] T. G. Ivanco, R. C. Scott, M. H. Love, S. Zink, and T. a. Weisshaar, “Validation of the Lockheed Martin morphing concept with wind tunnel testing,” vol. 23, p. 26, 2007. [7] S. Barbarino, O. Bilgen, R. M. Ajaj, M. I. Friswell, and D. J. Inman, “A Review of Morphing Aircraft,” J. Intell. Mater. Syst. Struct., vol. 22, no. 9, pp. 823–877, Aug. 2011. [8] T. A. Weisshaar and T. H. E. M. Challenge, “Morphing Aircraft Technology – New Shapes for Aircraft Design,” 2006. [9] R. M. Ajaj, C. S. Beaverstock, and M. I. Friswell, “Morphing aircraft: The need for a new design philosophy,” Aerosp. Sci. Technol., vol. 49, no. December 2017, pp. 154–166, 2015. [10] E. Kaygan and C. Ulusoy, “Effectiveness of Twist Morphing Wing on Aerodynamic Performance and Control of an Aircraft,” vol. 2, no. 2, pp. 77–86, 2018. [11] L. Prandtl, “Application of Modern Hydrodynamics to Aeronautics,” Naca, vol. 116, no. 116. 1923. [12] W. F. Phillips, N. R. Alley, and W. D. Goodrich, “Lifting-Line Analysis of Roll Control and Variable Twist,” J. Aircr., vol. 41, no. 5, pp. 1169–1176, 2004. [13] W. F. Phillips, S. R. Fugal, and R. E. Spall, “Minimizing Induced Drag with Wing Twist, Computational-Fluid-Dynamics Validation,” J. Aircr., vol. 43, no. 2, pp. 437–444, 2006. [14] D. Sahoo and C. Cesnik, “Roll maneuver control of UCAV wing using anisotropic piezoelectric actuators,” 43rd AIAA/ASME/ASCE/AHS/ASC Struct. Struct. Dyn. Mater. Conf., no. April, pp. 1–11, 2002. [15] D. A. N. Iii, D. J. Inman, and C. Woolsey, “Design , Development , and Analysis of a Morphing Aircraft Model for Wind Tunnel Experimentation by Design , Development , and Analysis of a Morphing Aircraft Model for Wind Tunnel Experimentation,” 2006. [16] H. Garcia, M. Abdulrahim, and R. Lind, “Roll Control for a Micro Air Vehicle Using Active Wing Morphing,” in AIAA Guidance, Navigation and Control Conference (Austin, TX), 2003, pp. 1–12. [17] M. Majji, “Design of a Morphing Wing : Modeling and Experiments,” Am. Inst. Aeronaut. Astronaut., p. 9, 2008. [18] R. Vos, Z. Gurdal, and M. Abdalla, “Mechanism for Warp-Controlled Twist of a Morphing Wing,” J. Aircr., vol. 47, no. 2, pp. 450–457, Mar. 2010. [19] H. Lv, J. Leng, and S. Du, “A Survey of Adaptive Materials and Structures Research in China,” in 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2009, no. May, pp. 1–8. [20] a. Y. N. Sofla, D. M. Elzey, and H. N. G. Wadley, “Two-way Antagonistic Shape Actuation Based on the One-way Shape Memory Effect,” J. Intell. Mater. Syst. Struct., vol. 19, no. 9, pp. 1017–1027, 2008. [21] D. M. Elzey, A. Y. N. Sofla, and H. N. G. Wadley, “A bio-inspired, high-authority actuator for shape morphing structures,” Proc. SPIE, vol. 5053, pp. 92–100, 2003. [22] B. K. Woods, O. Bilgen, and M. I. Friswell, “Wind tunnel testing of the fish bone active camber morphing concept,” J. Intell. Mater. Syst. Struct., vol. 25, no. 7, pp. 772–785, Feb. 2014. [23] R. Eppler, “Induced drag and winglets,” Aerosp. Sci. Technol., vol. 1, no. 1, pp. 3–15, 1997. [24] J. Guerrero, M. Sanguineti, and K. Wittkowski, “CFD Study of the Impact of Variable Cant Angle Winglets on Total Drag Reduction,” 2018. [25] N. M. Ursache, T. Melin, A. T. Isikveren, and M. I. Friswell, “Morphing Winglets for Aircraft Multi-phase Improvement,” 7th AIAA Aviat. Technol. Integr. Oper. Conf. ATIO May, no. September, pp. 18–20, 2007. [26] D. D. Smith, M. H. Lowenberg, D. P. Jones, M. I. Friswell, and S. Park, “COMPUTATIONAL AND EXPERIMENTAL ANALYSIS OF THE ACTIVE MORPHING WING CONCEPT,” 2012, pp. 1–9. [27] M. J. Smith, N. Komerath, R. Ames, O. Wong, and J.Pearson, “PERFORMANCE ANALYSIS OF A WING WITH MULTIPLE WINGLETS,” 2001. [28] a Beechook and J. Wang, “Aerodynamic Analysis of Variable Cant Angle Winglets for Improved Aircraft Performance,” no. September, pp. 13–14, 2013. [29] R. T. Whitcomb, “WIND-TUNNEL SUBSONIC MOUNTED APPROACH RESULTS SPEEDS FOR AND AT SELECTED WING-TIP WINGLETS NATIONAL AERONAUTICSAND SPACE ADMINISTRATION •,” Washington D. C., 1976. [30] R. Hallion, “NASA’s Contributions to Aeronautics: Aerodynamics, Structures, Propulsion, and Controls,” Washington, 2010. [31] P. Bourdin, A. Gatto, and M. I. Friswell, “Aircraft Control via Variable Cant-Angle Winglets,” Journal of Aircraft, vol. 45, no. 2. pp. 414–423, 2008. [32] P. Bourdin, A. Gatto, and M. I. Friswell, “Potential of Articulated Split Wingtips for Morphing-Based Control of a Flying Wing,” in 25th AIAA Applied Aerodynamics Conference, 2007, no. June, pp. 1–16. [33] a. Gatto, F. Mattioni, and M. I. Friswell, “Experimental Investigation of Bistable Winglets to Enhance Aircraft Wing Lift Takeoff Capability,” J. Aircr., vol. 46, no. 2, pp. 647–655, Mar. 2009. [34] E. Kaygan and A. Gatto, “Investigation of Adaptable Winglets for Improved UAV Control and Performance,” Int. J. Mech. Aerospace, Ind. Mechatronics Eng., vol. 8, no. 7, pp. 1281–1286, 2014. [35] E. Kaygan and A. Gatto, “Computational Analysis of Adaptable Winglets for Improved Morphing Aircraft Performance,” Int. J. Aerosp. Mech. Eng., vol. 9, no. 7, pp. 1127–1133, 2015. [36] E. Kaygan and A. Gatto, “Development of an Active Morphing Wing With Adaptive Skin for Enhanced Aircraft Control and Performance,” in Greener Aviation 2016, 2016, no. October. [37] E. and Kaygan and A. Gatto, “Structural Analysis of an Active Morphing Wing for Enhancing UAV Performance,” vol. 12, no. 10, pp. 948–955, 2018. [38] A. Gatto and E. Kaygan, “BLADE OR WING,” WO/2018/046936. [39] C. Thill, J. Etches, I. Bond, K. Potter, and P. Weaver, “Morphing skins,” no. 3216, pp. 1–23, 2008. [40] Airbus S.A.S., “Aircraft Characteristics Airport and Maintenance Planning (A330-300/-800),” France, 2018. [41] H. H. Açıkel, “An experimental study on aerodynamics of NACA2415 aerofoil at low Re numbers,” Exp. Therm. Fluid Sci., vol. 39, pp. 252–264, 2012. [42] M. Drela and H. Youngren, “Project 4 – Aircraft Aerodynamic Characteristics,” pp. 1–7. [43] C. E. Lan, “A quasi-vortex-lattice method in thin wing theory,” vol. 11, no. 9, 1974. [44] P. G. Saffman, Vortex Dynamics Cambridge. England, U.K.: Cambridge Univ. Press, 1992. [45] W. F. Phillips, “Lifting-Line Analysis for Twisted Wings and Washout-Optimized Wings,” J. Aircr., vol. 41, no. 1, pp. 128–136, 2004. [46] D. D. Smith, M. H. Lowenberg, D. P. Jones, and M. I. Friswell, “Computational and Experimental Validation of the Active Morphing Wing,” J. Aircr., vol. 51, no. 3, pp. 925–937, May 2014. [47] P. Bourdin, A. . Gatto, and M. Friswell, “The Application of Variable Cant Angle Winglets for Morphing Aircraft Control,” in 24th Applied Aerodynamics Conference, 2006, no. June, pp. 1–13. [48] A. Bolonkin and G. Gilyard, “Estimated Benefits of Variable-Geometry Wing Camber Control for Transport Aircraft,” Tech. Memo. NASA Dryden Flight Res. Cent., no. October 1999, 2018. [49] Q. Wang, Y. Chen, and H. Tang, “Mechanism Design for Aircraft Morphing Wing,” 53rd AIAA/ASME/ASCE/AHS/ASC Struct. Struct. Dyn. Mater. Conf. AIAA/ASME/AHS Adapt. Struct. Conf. AIAA, no. October, 2012. [50] M. Sanguineti and K. Wittkowski, “V ariable cant angle winglets for improvement of aircraft flight performance,” no. July, 2019.

Geliştirilmiş Ticari Uçak Performansı için Uyarlanabilen Kanatçıkların Aerodinamik Analizi

Yıl 2020, , 31 - 44, 24.06.2020
https://doi.org/10.30518/jav.716194

Öz

This article describes the performance benefits of variable winglet configurations. The primary variables investigated involved varying the winglet twist and dihedral angle of a comparable Airbus A330-300 wing structure. Numerical studies have been carried out in AVL (Athena Vortex Lattice Method). In order to illustrate the aerodynamic benefits of morphing winglet concepts for different flight regimes, values of twist (-10°< θ <10°, in steps of ±2.5°) and values of dihedral (-90°< θ <90°, in steps of ±15°) were designed and numerically investigated. The results obtained from this work indicate that by carefully adjusting morphing winglets on air vehicles (Airbus A330-300), the aerodynamic performance benefits could be achieved.

Kaynakça

  • [1] A. R. et al McGowan, “Recent Results from NASA’s Morphing Project,” in 9th International Symposium on Smart Structure and Materials, 2002, p. SPIE PaperNo.4698-11. [2] T. a. Weisshaar, “Morphing Aircraft Systems: Historical Perspectives and Future Challenges,” J. Aircr., vol. 50, no. 2, pp. 337–353, 2013. [3] D. McRuer and D. Graham, “Flight Control Century: Triumphs of the Systems Approach,” J. Guid. Control. Dyn., vol. 27, no. 2, pp. 161–173, 2004. [4] E. Wilson, “Nature photography,” Nature, vol. 82, no. 2100, pp. 371–372, 1910. [5] NASA, “21st Century Aerospace Vehicle, Morphing Airplane.” . [6] T. G. Ivanco, R. C. Scott, M. H. Love, S. Zink, and T. a. Weisshaar, “Validation of the Lockheed Martin morphing concept with wind tunnel testing,” vol. 23, p. 26, 2007. [7] S. Barbarino, O. Bilgen, R. M. Ajaj, M. I. Friswell, and D. J. Inman, “A Review of Morphing Aircraft,” J. Intell. Mater. Syst. Struct., vol. 22, no. 9, pp. 823–877, Aug. 2011. [8] T. A. Weisshaar and T. H. E. M. Challenge, “Morphing Aircraft Technology – New Shapes for Aircraft Design,” 2006. [9] R. M. Ajaj, C. S. Beaverstock, and M. I. Friswell, “Morphing aircraft: The need for a new design philosophy,” Aerosp. Sci. Technol., vol. 49, no. December 2017, pp. 154–166, 2015. [10] E. Kaygan and C. Ulusoy, “Effectiveness of Twist Morphing Wing on Aerodynamic Performance and Control of an Aircraft,” vol. 2, no. 2, pp. 77–86, 2018. [11] L. Prandtl, “Application of Modern Hydrodynamics to Aeronautics,” Naca, vol. 116, no. 116. 1923. [12] W. F. Phillips, N. R. Alley, and W. D. Goodrich, “Lifting-Line Analysis of Roll Control and Variable Twist,” J. Aircr., vol. 41, no. 5, pp. 1169–1176, 2004. [13] W. F. Phillips, S. R. Fugal, and R. E. Spall, “Minimizing Induced Drag with Wing Twist, Computational-Fluid-Dynamics Validation,” J. Aircr., vol. 43, no. 2, pp. 437–444, 2006. [14] D. Sahoo and C. Cesnik, “Roll maneuver control of UCAV wing using anisotropic piezoelectric actuators,” 43rd AIAA/ASME/ASCE/AHS/ASC Struct. Struct. Dyn. Mater. Conf., no. April, pp. 1–11, 2002. [15] D. A. N. Iii, D. J. Inman, and C. Woolsey, “Design , Development , and Analysis of a Morphing Aircraft Model for Wind Tunnel Experimentation by Design , Development , and Analysis of a Morphing Aircraft Model for Wind Tunnel Experimentation,” 2006. [16] H. Garcia, M. Abdulrahim, and R. Lind, “Roll Control for a Micro Air Vehicle Using Active Wing Morphing,” in AIAA Guidance, Navigation and Control Conference (Austin, TX), 2003, pp. 1–12. [17] M. Majji, “Design of a Morphing Wing : Modeling and Experiments,” Am. Inst. Aeronaut. Astronaut., p. 9, 2008. [18] R. Vos, Z. Gurdal, and M. Abdalla, “Mechanism for Warp-Controlled Twist of a Morphing Wing,” J. Aircr., vol. 47, no. 2, pp. 450–457, Mar. 2010. [19] H. Lv, J. Leng, and S. Du, “A Survey of Adaptive Materials and Structures Research in China,” in 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2009, no. May, pp. 1–8. [20] a. Y. N. Sofla, D. M. Elzey, and H. N. G. Wadley, “Two-way Antagonistic Shape Actuation Based on the One-way Shape Memory Effect,” J. Intell. Mater. Syst. Struct., vol. 19, no. 9, pp. 1017–1027, 2008. [21] D. M. Elzey, A. Y. N. Sofla, and H. N. G. Wadley, “A bio-inspired, high-authority actuator for shape morphing structures,” Proc. SPIE, vol. 5053, pp. 92–100, 2003. [22] B. K. Woods, O. Bilgen, and M. I. Friswell, “Wind tunnel testing of the fish bone active camber morphing concept,” J. Intell. Mater. Syst. Struct., vol. 25, no. 7, pp. 772–785, Feb. 2014. [23] R. Eppler, “Induced drag and winglets,” Aerosp. Sci. Technol., vol. 1, no. 1, pp. 3–15, 1997. [24] J. Guerrero, M. Sanguineti, and K. Wittkowski, “CFD Study of the Impact of Variable Cant Angle Winglets on Total Drag Reduction,” 2018. [25] N. M. Ursache, T. Melin, A. T. Isikveren, and M. I. Friswell, “Morphing Winglets for Aircraft Multi-phase Improvement,” 7th AIAA Aviat. Technol. Integr. Oper. Conf. ATIO May, no. September, pp. 18–20, 2007. [26] D. D. Smith, M. H. Lowenberg, D. P. Jones, M. I. Friswell, and S. Park, “COMPUTATIONAL AND EXPERIMENTAL ANALYSIS OF THE ACTIVE MORPHING WING CONCEPT,” 2012, pp. 1–9. [27] M. J. Smith, N. Komerath, R. Ames, O. Wong, and J.Pearson, “PERFORMANCE ANALYSIS OF A WING WITH MULTIPLE WINGLETS,” 2001. [28] a Beechook and J. Wang, “Aerodynamic Analysis of Variable Cant Angle Winglets for Improved Aircraft Performance,” no. September, pp. 13–14, 2013. [29] R. T. Whitcomb, “WIND-TUNNEL SUBSONIC MOUNTED APPROACH RESULTS SPEEDS FOR AND AT SELECTED WING-TIP WINGLETS NATIONAL AERONAUTICSAND SPACE ADMINISTRATION •,” Washington D. C., 1976. [30] R. Hallion, “NASA’s Contributions to Aeronautics: Aerodynamics, Structures, Propulsion, and Controls,” Washington, 2010. [31] P. Bourdin, A. Gatto, and M. I. Friswell, “Aircraft Control via Variable Cant-Angle Winglets,” Journal of Aircraft, vol. 45, no. 2. pp. 414–423, 2008. [32] P. Bourdin, A. Gatto, and M. I. Friswell, “Potential of Articulated Split Wingtips for Morphing-Based Control of a Flying Wing,” in 25th AIAA Applied Aerodynamics Conference, 2007, no. June, pp. 1–16. [33] a. Gatto, F. Mattioni, and M. I. Friswell, “Experimental Investigation of Bistable Winglets to Enhance Aircraft Wing Lift Takeoff Capability,” J. Aircr., vol. 46, no. 2, pp. 647–655, Mar. 2009. [34] E. Kaygan and A. Gatto, “Investigation of Adaptable Winglets for Improved UAV Control and Performance,” Int. J. Mech. Aerospace, Ind. Mechatronics Eng., vol. 8, no. 7, pp. 1281–1286, 2014. [35] E. Kaygan and A. Gatto, “Computational Analysis of Adaptable Winglets for Improved Morphing Aircraft Performance,” Int. J. Aerosp. Mech. Eng., vol. 9, no. 7, pp. 1127–1133, 2015. [36] E. Kaygan and A. Gatto, “Development of an Active Morphing Wing With Adaptive Skin for Enhanced Aircraft Control and Performance,” in Greener Aviation 2016, 2016, no. October. [37] E. and Kaygan and A. Gatto, “Structural Analysis of an Active Morphing Wing for Enhancing UAV Performance,” vol. 12, no. 10, pp. 948–955, 2018. [38] A. Gatto and E. Kaygan, “BLADE OR WING,” WO/2018/046936. [39] C. Thill, J. Etches, I. Bond, K. Potter, and P. Weaver, “Morphing skins,” no. 3216, pp. 1–23, 2008. [40] Airbus S.A.S., “Aircraft Characteristics Airport and Maintenance Planning (A330-300/-800),” France, 2018. [41] H. H. Açıkel, “An experimental study on aerodynamics of NACA2415 aerofoil at low Re numbers,” Exp. Therm. Fluid Sci., vol. 39, pp. 252–264, 2012. [42] M. Drela and H. Youngren, “Project 4 – Aircraft Aerodynamic Characteristics,” pp. 1–7. [43] C. E. Lan, “A quasi-vortex-lattice method in thin wing theory,” vol. 11, no. 9, 1974. [44] P. G. Saffman, Vortex Dynamics Cambridge. England, U.K.: Cambridge Univ. Press, 1992. [45] W. F. Phillips, “Lifting-Line Analysis for Twisted Wings and Washout-Optimized Wings,” J. Aircr., vol. 41, no. 1, pp. 128–136, 2004. [46] D. D. Smith, M. H. Lowenberg, D. P. Jones, and M. I. Friswell, “Computational and Experimental Validation of the Active Morphing Wing,” J. Aircr., vol. 51, no. 3, pp. 925–937, May 2014. [47] P. Bourdin, A. . Gatto, and M. Friswell, “The Application of Variable Cant Angle Winglets for Morphing Aircraft Control,” in 24th Applied Aerodynamics Conference, 2006, no. June, pp. 1–13. [48] A. Bolonkin and G. Gilyard, “Estimated Benefits of Variable-Geometry Wing Camber Control for Transport Aircraft,” Tech. Memo. NASA Dryden Flight Res. Cent., no. October 1999, 2018. [49] Q. Wang, Y. Chen, and H. Tang, “Mechanism Design for Aircraft Morphing Wing,” 53rd AIAA/ASME/ASCE/AHS/ASC Struct. Struct. Dyn. Mater. Conf. AIAA/ASME/AHS Adapt. Struct. Conf. AIAA, no. October, 2012. [50] M. Sanguineti and K. Wittkowski, “V ariable cant angle winglets for improvement of aircraft flight performance,” no. July, 2019.
Toplam 1 adet kaynakça vardır.

Ayrıntılar

Birincil Dil İngilizce
Konular Uzay Mühendisliği
Bölüm Araştırma Makaleleri
Yazarlar

Erdogan Kaygan 0000-0003-3319-3657

Yayımlanma Tarihi 24 Haziran 2020
Gönderilme Tarihi 8 Nisan 2020
Kabul Tarihi 7 Haziran 2020
Yayımlandığı Sayı Yıl 2020

Kaynak Göster

APA Kaygan, E. (2020). Aerodynamic Analysis of Morphing Winglets for Improved Commercial Aircraft Performance. Journal of Aviation, 4(1), 31-44. https://doi.org/10.30518/jav.716194

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