Comparison on the Aerodynamic Coefficients Obtained from Three Different Size of Wind Tunnel Model on Baseline V Set at 45 Degree Sweep Tail Angle

  • Abstract
  • Keywords
  • References
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  • Abstract

    This paper analyzes the aerodynamic coefficients of a blended wing body, Baseline V which is equipped with 45˚ sweep tail angle. Baseline V is one of the Universiti Teknologi MARA (UiTM) Shah Alam Flight Test Technology Centre’s blended wing body designs that have unique configuration as it uses different NACA airfoil for its fuselage, body, wing root, midwing, wingtip, tail root, and tail tip. The intention of the comparison for three different size of wind tunnel model is to determine the similarity of the aerodynamics coefficients and the behaviour of the model itself. The wind tunnel experiments were conducted at three different wind tunnel locations: Universiti Teknologi Malaysia Skudai, UiTM Shah Alam and Universiti Pertahan Nasional Malaysia Kuala Lumpur, using 1:1 scale full model, 1:2 scale half model, and 2:7 scale half model, respectively. The data obtained are studied and plotted in term of lift coefficients, lift-to-drag ratio, and drag coefficients. The pitching angle for all experiments were varied between -10˚ to +17˚. The blockage corrections have been applied to the data to obtain the actual performance of the aircraft. From the observations, the results show some similarity between those experiments, except for the lift-to-drag ratio of UPNM’s data which are slightly higher compared to others.


  • Keywords

    Aerodynamics; Blended Wing Body; Wind Tunnel Experiments.

  • References

      [1] R. H. Liebeck, "Design of the Blended Wing Body Subsonic Transport,," Journal of Aircraft, vol. 41, pp. 10-25, 2004.

      [2] J. D. Anderson, Aircraft performance and design: McGraw-Hill Science/Engineering/Math, 1999.

      [3] M. A. Page, M. A. Potsdam, R. H. Liebeck., "Blended wing body analysis and design[J]," AIAA Paper, p. 2317: 1997, 1997.

      [4] R. H. Liebeck, "Design of the blended wing body subsonic transport[J]." Journal of Aircraft, pp. 41(1): 10-25., 2004.

      [5] J. van Dommelen and R. Vos, "Conceptual design and analysis of blended-wing-body aircraft," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 228, pp. 2452-2474, 2014/11/01 2014.

      [6] M. Voskuijl, G. La Rocca, and F. Dircken, "Controllability of blended wing body aircraft," in 26th International Congress of the Aeronautical Sciences, 2008, pp. 14-19.

      [7] S. Siouris and N. Qin, "Study of the effects of wing sweep on the aerodynamic performance of a blended wing body aircraft," Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, vol. 221, pp. 47-55, 2007/01/01 2007.

      [8] N. Qin, Vavalle, A., Le Moigne, A., Laban, M., Hackett, K., and Weinnerfelt, P, "Aerodynamic Considerations of Blended Wing Body Aircraft," Progress in Aerospace Science,, pp. 321-343, 2004.

      [9] P. Li, B. Zhang, Y. Chen, C. Yuan, and Y. Lin, "Aerodynamic Design Methodology for Blended Wing Body Transport," Chinese Journal of Aeronautics, vol. 25, pp. 508-516, 2012.

      [10] Z. Lyu and J. R. R. A. Martins, "Aerodynamic Design Optimization Studies of a Blended-Wing-Body Aircraft," Journal of Aircraft, vol. 51, pp. 1604-1617, 2014/09/01 2014.

      [11] H. Engels, W. Becker, and A. Morris, "Implementation of a multi-level optimisation methodology within the e-design of a blended wing body," Aerospace Science and Technology, vol. 8, pp. 145-153, 2004/03/01/ 2004.

      [12] R. Wittmann, "Passenger acceptance of BWB configurations," in Proceedings of the 24th ICAS Congress, Yokohama, Japan, 2004.

      [13] R. C. Odle, D. Roman, and B. K. Rawdon, "Blended wing body cargo airplane," ed: Google Patents, 2011.

      [14] Boeing. (2017). Blended Wing Body Goes with the Flow in New Visualization Test, .

      [15] Prof. E. G. Tulapurkara, "Airplane design(Aerodynamic) ", ed: Dept. of Aerospace Engg., Indian Institute of Technology, Madras, 2013.

      [16] W. Kuntjoro, Rizal E.M. Nasir, W. Wisnoe, "Aerodynamic, stability and flying quality evaluation on a small blended wing-body aircraft with canard foreplanes," Procedia Technology 15, pp. 783-791, 2014.

      [17] W. Wisnoe, R. Effendy, M. Nasir, W. Kuntjoro, A. Mohd, and A. Bin Mamat, Wind Tunnel Experiments and CFD Analysis of Blended Wing Body (BWB) Unmanned Aerial Vehicle (UAV) at Mach 0.1 and Mach 0.3, 0002.

      [18] W. Kuntjoro, Rizal E M Nasir, Wirachman Wisnoe, Zurriati Ali, "Longitudinal Flight Dynamics of Baseline-II BWB UAV," Advanced Materials Research, vol. 433-440, pp. 6636-6640, 2012.

      [19] Rizal E. M. Nasir. Wirachman Wisnoe, Ramzyzan Ramly, Wahyu Kuntjoroa, Firdaus Muhammad, “Aerodynamic of UiTM’s Blended-Wing-Body Unmanned Aerial Vehicle Baseline-II Equipped with One Central Vertical Rudder,” Jurnal Teknologi, vol. 12, pp. 133-139, 2015.

      [20] M. Z. A. A. Latif, M. A. Ahmad, R. E. M. Nasir, W. Wisnoe, and M. R. Saad, "An analysis on 45° sweep tail angle for blended wing body aircraft to the aerodynamics coefficients by wind tunnel experiment," IOP Conference Series: Materials Science and Engineering, vol. 270, p. 012001, 2017.

      [21] Ross and A. Altman, "Wind tunnel blockage corrections: Review and application to Savonius vertical-axis wind turbines," Journal of Wind Engineering and Industrial Aerodynamics, vol. 99, pp. 523-538, 2011/05/01/ 2011.

      [22] Etkin, B. and L.D. Reid, Dynamics of flight: stability and control. Vol. 3. 1996: Wiley New York.

      [23] Anderson, J.D., Aircraft performance and design. 1999: McGraw-Hill Science/Engineering/Math.

      [24] Hoerner, S.F. and H.V. Borst, Fluid-dynamic lift: practical information on aerodynamic and hydrodynamic lift. 1985: LA Hoerner.

      [25] Brumbaugh, R.W., Aircraft model for the AIAA controls design challenge. Journal of guidance, control, and dynamics, 1994. 17(4): p. 747-752.




Article ID: 22248
DOI: 10.14419/ijet.v7i4.25.22248

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