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<p>The NACA 66-210 airfoil was created to reduce drag and preserve extended laminar flow for high-speed aircraft applications. With a rearward-thickness distribution and a maximum chord thickness of 10%, it provides an acceptable balance between structural integrity and aerodynamic efficiency. By postponing drag rise and flow separation, its smooth shape and advantageous pressure gradient help it operate efficiently in the transonic flow regime. This study presents the aerodynamic performance enhancement of NACA 66-210 airfoil for supersonic flow by channeling through it and compares the performance with the baseline airfoil. A series of simulations is performed for various Mach numbers and angles of attack to investigate the possibility of reducing the drag and enhancing the lift-to-drag ratio by changing the channel heights. The result shows that a NACA 66-210 airfoil with 18% channel height demonstrates a 28.32% reduction in drag coefficient and a 28.42% enhancement in lift-to-drag ratio in comparison with baseline airfoil. The effect of the Mach number variation for a fixed channel height (12%) was evaluated. The drag coefficient rises with the increase of the angle of attack, whereas it decreases for higher values of Mach number. Moreover, NACA 66-210 airfoil with a thick round channel (2&#xa0;mm fillet radius in 12% thick sharp channeled airfoil) has been compared with a similar type of thick sharp channel for different Mach numbers and fixed angle of attack. The airfoil with a thick round channel has a lower drag coefficient than a baseline airfoil but higher than the thick sharp channeled airfoil. Consequently, the round channeled airfoil produced a higher lift-to-drag ratio than a baseline airfoil but lower than a sharp channeled airfoil. The percentage reduction of the drag coefficient is 8.124% for a thick round channeled airfoil and 21.43% for a thick sharp channeled airfoil compared to the baseline airfoil.</p>

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Aerodynamic Performance Investigation of Supersonic Airfoil Design by Channeling NACA 66-210

  • 期刊论文

  • 发表日期：

    2025年8月21日

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  • S. M. Enamul Hoque Yasin,
  • Md Ashraful Islam,
  • Abdullah Al-Faruk

摘要

The NACA 66-210 airfoil was created to reduce drag and preserve extended laminar flow for high-speed aircraft applications. With a rearward-thickness distribution and a maximum chord thickness of 10%, it provides an acceptable balance between structural integrity and aerodynamic efficiency. By postponing drag rise and flow separation, its smooth shape and advantageous pressure gradient help it operate efficiently in the transonic flow regime. This study presents the aerodynamic performance enhancement of NACA 66-210 airfoil for supersonic flow by channeling through it and compares the performance with the baseline airfoil. A series of simulations is performed for various Mach numbers and angles of attack to investigate the possibility of reducing the drag and enhancing the lift-to-drag ratio by changing the channel heights. The result shows that a NACA 66-210 airfoil with 18% channel height demonstrates a 28.32% reduction in drag coefficient and a 28.42% enhancement in lift-to-drag ratio in comparison with baseline airfoil. The effect of the Mach number variation for a fixed channel height (12%) was evaluated. The drag coefficient rises with the increase of the angle of attack, whereas it decreases for higher values of Mach number. Moreover, NACA 66-210 airfoil with a thick round channel (2 mm fillet radius in 12% thick sharp channeled airfoil) has been compared with a similar type of thick sharp channel for different Mach numbers and fixed angle of attack. The airfoil with a thick round channel has a lower drag coefficient than a baseline airfoil but higher than the thick sharp channeled airfoil. Consequently, the round channeled airfoil produced a higher lift-to-drag ratio than a baseline airfoil but lower than a sharp channeled airfoil. The percentage reduction of the drag coefficient is 8.124% for a thick round channeled airfoil and 21.43% for a thick sharp channeled airfoil compared to the baseline airfoil.