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<p>The present study focuses on improving the aerodynamic performance of airfoils for micro and small-capacity wind turbines in developing countries, where low Reynolds number (<i>Re</i>) flow conditions often cause laminar separation. Two new airfoils, INDTH7 (thin) and INDTH12 (thick) were designed specifically for Indian environmental conditions and tested in computational models. These airfoils were compared to NACA2408 and SD6060, commonly used in low <i>Re</i> applications. Results show that the airfoils INDTH7 and INDTH12 outperformed existing ones, with higher lift-to-drag ratios and stall angles. The optimum lift-to-drag ratios for INDTH12, INDTH7, NACA2408, and SD6060 were 112, 101, 87, and 94, respectively, while stall angles were 9.5° for INDTH12, 11.5° for INDTH7, 10.5° for NACA2408, and 11° for SD6060. The power coefficient vs. tip speed ratio performance of the INDTH7 and INDTH12 airfoils differed significantly from existing ones, with INDTH12 achieving a peak power coefficient of 0.551 at TSR 5, and INDTH7 reaching 0.556 at TSR 8. Additionally, there were minimal variations in lift performance for INDTH7 and INDTH12, making them suitable for low <i>Re</i> applications. These airfoils, optimized with a thickness-to-camber ratio (<i>t</i>/<i>c</i>) between 0.875 and 3.5, address the challenge of laminar separation in micro and small-sized wind turbine blades, enhancing overall performance in household energy generation systems. The new airfoils were studied computationally using Ansys Fluent for turbulent, two-dimensional, steady, incompressible fluid flow. The standard airfoil SG6043 was selected to validate the computational domain against available experimental wind tunnel results. The error in the CFD results was approximately 4% compared to the experimental data, thus validating the computational domain used for CFD studies of the new airfoils, INDTH7 and INDTH12. The AOAs viz<i>.</i> 3.5°, 5°, and 6.5°represented the optimum angles for the airfoils SG6043, INDTH7, and INDTH12 respectively, at which the highest lift-to-drag ratios were obtained.</p>

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Development of Two New Airfoils for Micro-Capacity Wind Turbine Application

  • 期刊论文

  • 发表日期：

    2025年7月5日

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  • Minendra L. Surve,
  • Prashant D. Deshmukh,
  • Kailasnath B. Sutar,
  • Bharatbhushan S. Kale,
  • Satish M. Silaskar,
  • Kiran Suresh Bhole

摘要

The present study focuses on improving the aerodynamic performance of airfoils for micro and small-capacity wind turbines in developing countries, where low Reynolds number (Re) flow conditions often cause laminar separation. Two new airfoils, INDTH7 (thin) and INDTH12 (thick) were designed specifically for Indian environmental conditions and tested in computational models. These airfoils were compared to NACA2408 and SD6060, commonly used in low Re applications. Results show that the airfoils INDTH7 and INDTH12 outperformed existing ones, with higher lift-to-drag ratios and stall angles. The optimum lift-to-drag ratios for INDTH12, INDTH7, NACA2408, and SD6060 were 112, 101, 87, and 94, respectively, while stall angles were 9.5° for INDTH12, 11.5° for INDTH7, 10.5° for NACA2408, and 11° for SD6060. The power coefficient vs. tip speed ratio performance of the INDTH7 and INDTH12 airfoils differed significantly from existing ones, with INDTH12 achieving a peak power coefficient of 0.551 at TSR 5, and INDTH7 reaching 0.556 at TSR 8. Additionally, there were minimal variations in lift performance for INDTH7 and INDTH12, making them suitable for low Re applications. These airfoils, optimized with a thickness-to-camber ratio (t/c) between 0.875 and 3.5, address the challenge of laminar separation in micro and small-sized wind turbine blades, enhancing overall performance in household energy generation systems. The new airfoils were studied computationally using Ansys Fluent for turbulent, two-dimensional, steady, incompressible fluid flow. The standard airfoil SG6043 was selected to validate the computational domain against available experimental wind tunnel results. The error in the CFD results was approximately 4% compared to the experimental data, thus validating the computational domain used for CFD studies of the new airfoils, INDTH7 and INDTH12. The AOAs viz. 3.5°, 5°, and 6.5°represented the optimum angles for the airfoils SG6043, INDTH7, and INDTH12 respectively, at which the highest lift-to-drag ratios were obtained.