Commenced in January 2007
Paper Count: 30184
Application of Fuzzy Logic Approach for an Aircraft Model with and without Winglet
Abstract:The measurement of aerodynamic forces and moments acting on an aircraft model is important for the development of wind tunnel measurement technology to predict the performance of the full scale vehicle. The potentials of an aircraft model with and without winglet and aerodynamic characteristics with NACA wing No. 65-3- 218 have been studied using subsonic wind tunnel of 1 m × 1 m rectangular test section and 2.5 m long of Aerodynamics Laboratory Faculty of Engineering (University Putra Malaysia). Focusing on analyzing the aerodynamic characteristics of the aircraft model, two main issues are studied in this paper. First, a six component wind tunnel external balance is used for measuring lift, drag and pitching moment. Secondly, Tests are conducted on the aircraft model with and without winglet of two configurations at Reynolds numbers 1.7×105, 2.1×105, and 2.5×105 for different angle of attacks. Fuzzy logic approach is found as efficient for the representation, manipulation and utilization of aerodynamic characteristics. Therefore, the primary purpose of this work was to investigate the relationship between lift and drag coefficients, with free-stream velocities and angle of attacks, and to illustrate how fuzzy logic might play an important role in study of lift aerodynamic characteristics of an aircraft model with the addition of certain winglet configurations. Results of the developed fuzzy logic were compared with the experimental results. For lift coefficient analysis, the mean of actual and predicted values were 0.62 and 0.60 respectively. The coreelation between actual and predicted values (from FLS model) of lift coefficient in different angle of attack was found as 0.99. The mean relative error of actual and predicted valus was found as 5.18% for the velocity of 26.36 m/s which was found to be less than the acceptable limits (10%). The goodness of fit of prediction value was 0.95 which was close to 1.0.
Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1063206Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 1513
 R.T.Whitcomb, A Design Approach and Selected Wind-Tunnel Results at High Subsonic Speeds for Wing-Tip Mounted Winglets, NASA TN D- 8260, 1976.
 R. T. Whitcomb, Methods for Reducing Aerodynamic Drag, NASA Conference Publication 2211, Proceedings of Dryden Symposium, Edwards, California, 1981.
 J. E.Yates, and C. Donaldson, Fundamental Study of Drag and an Assessment of Conventional Drag-Due-To-Lift Reduction Devices, NASA Contract Rep 4004, 1986.
 B. Louis, Gratzer, Spiroid-Tipped Wing. U. S. patent 5, 102,068, 1992.
 V. F. Reginald, Vortex Reducing Wing Tip, U. S. Patent 4, 108, 403, 1978.
 R. T. Jones, Improving the Efficiency of Smaller Transport Aircraft, 14th Congress of the International Council of the Aeronautical Sciences, proceeding, Vol. 1, Toulouse, Fr. 1984.
 Chandrasekharan, M. Reuben, Murphy, R. William, Taverna, P. Frank, and B. W. Charles, Computational Aerodynamic Design of the Gulftream IV Wing, AIAA-85-0427, 1985..
 M. D. Maughmer, S. S. Tmothy, and S. M. Willits, The Design and Testing of a Winglet Airfoil for Low-Speed Aircraft, AIAA Paper 2001- 2478, 2001.
 J. J. Spillman, The use of wing tip sails to reduce vortex drag, Aeronautical Journal, September, pp. 387-395, 1978.
 J. J. Spillman, H. Y. Ratcliffe, and A. McVitie, Flight experiments to evaluate the effect of wing-tip sails on fuel consumption and handling characteristics, Aeronautical Journal, July, pp. 279-281, 1979.
 J. J. Spillman, and M. J. Fell, The effects of wing tip devices on (a) the performance of the Bae Jetstream (b) the far-field wake of a Paris Aircraft, Paper 31A, AGARD CP No. 342, Aerodynamics of Vortical Type Flows in Three Dimensions, April, pp. 31A-1-11, 1983.
 H. G. Klug, Auxiliary Wing Tips for an Aircraft, U. S. Patent 4722499, 1988.
 A.T. Vance, Gliding Birds: Reduction of Induced Drag by Wing Tip Slots between the Primary Feathers, Journal of Experimental Biology, Vol. 180 (1), pp. 285-310, 1993.
 M. J. Smith, N. Komerath, R. Ames, O. Wong, and J. Pearson, Performance Analysis of a Wing with Multiple Winglets, AIAA Paper- 2001-2407, 2001.
 L. U. Roche, and S. Palffy, WING-GRID, a Novel Device for Reduction of Induced Drag on Wings, Proceedings of ICAS 96, Sorrento, September, 1996.
 A. Hossain, P. R. Arora, A. Rahman, A. A. Jaafar, and A. K. M. P. Iqbal, Analysis of Aerodynamic Characteristics of an Aircraft Model with and Without Winglet, Jordan Journal of Mechanical and Industrial Engineering. Vol. 2, No. 3, pp. 143-150, 2008.
 R. A. Prithvi, A. Hossain, A. A. Jaafar, P. Edi, T. S. Younis, and M. Saleem, Drag Reduction in Aircraft Model using Elliptical Winglet, Journal - The Institution of Engineers, Malaysia (IEM), Vol. 66, No. 4, pp. 1-8, 2005.
 P. R. Arora, A. Hossain, P. Edi, A. A. Jaafar, T.S. Younis, and M. Saleem, Six-Component External Balance: A Calibration Study, Proceedings of AEROTECH-2005, Putra Jaya, Malaysia.
 A. Hossain, R. Ataur, M. Rahman, SK. Hasan, and H. Jakir, Prediction of Power Generation of Small Scale Vertical Axis Wind Turbine Using Fuzzy Logic, Journal of Urban and Environmental Engineering (JUEE), Vol. 3, No.2, pp. 43-51, 2009.
 A. Al-Anbuky, S. Bataineh, and S. Al-Aqtash, Power demand prediction using fuzzy logic, Control Engineering Practice, Vol. 3, No. 9, pp. 1291- 1298, 1995.
 K. Carman, Prediction of soil compaction under pneumatic tires a using fuzzy logic approach, Journal of Terramechanics, Vol.45, pp.103-108, 2008.
 K.M. Passino, and S. Yurkovich, Fuzzy control, Addison Wesley Longman, Inc. Menlo park, CA, USA, 1998.
 J. J. Bertin, Aerodynamics for Engineers. New Jersey, Prentice-Hall, Inc. 2002.
 A. Hossain, P. R. Arora, A. Rahman, A. A. Jaafar, A.K.M.P. Iqbal, and M. Ariffin, Lift Analysis of an Aircraft Model with and without Winglet, 7th International Conference on Mechanical Engineering, ICME 2007, 28-30 December, 2007, Dhaka, Bangladesh.
 A. Rajagopalan, G. Washington, G. Rizzani, and Y. Guezennec, Development of Fuzzy Logic and Neural Network Control and Advanced Emissions Modeling for Parallel Hybrid Vehicles, Center for Automotive Research, Intelligent Structures and Systems Laboratory, Ohio State University, USA, December 2003.