Feasibility study of power generation using a turbine mounted in aircraft wing

  • Authors

    • K. Sri Vamsi Krishna Department of Aeronautical Engineering.Institute of Aeronautical Engineering, Dundigal 500043
    • Shiva Prasad Department of Aeronautical Engineering.Institute of Aeronautical Engineering, Dundigal 500043
    • R. Sabari Vihar Department of Aeronautical Engineering.Institute of Aeronautical Engineering, Dundigal 500043
    • K. Babitha Department of Aeronautical Engineering.Institute of Aeronautical Engineering, Dundigal 500043
    • K Veeranjaneyulu Department of Aeronautical Engineering.MLR Institute of Technology, Dundigal 500043
    • Govardhan D. Department of Aeronautical Engineering.Institute of Aeronautical Engineering, Dundigal 500043
    2018-03-23
    https://doi.org/10.14419/ijet.v7i2.9196
  • Aircraft, Angle of Attack, Flow Visualization, Feasibility, Power, Turbine, Wing.

  • Abstract

    The main objective of this study is to increase the aerodynamic efficiency of turbine mounted novel wing. The main motive behind this work is to reduce the drag by attaining the positive velocity gradient and generate power by converting the stagnation pressure which also acts as emergency power source. By using the energy source of free stream air, Mechanical energy is converted into electrical energy. The obtained power is presented in terms of voltage generated at various angles of attack with different Reynolds number. Experimental analysis is carried out for NACA4415 airfoil at various angles with respect to free stream ranging from 0deg to 30deg from laminar to turbulent Reynolds number. The results were obtained using the research tunnel at IARE aerodynamic facility center. The aerodynamic advantage of this design in terms of voltage is 9.5 V at 35m/s which can be utilized for the aircraft on board power systems.

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  • How to Cite

    Krishna, K. S. V., Prasad, S., Vihar, R. S., Babitha, K., Veeranjaneyulu, K., & D., G. (2018). Feasibility study of power generation using a turbine mounted in aircraft wing. International Journal of Engineering & Technology, 7(2), 433-436. https://doi.org/10.14419/ijet.v7i2.9196

    Received date: 2018-01-17

    Accepted date: 2018-03-01

    Published date: 2018-03-23