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<p>In this study, we conducted numerical simulations of a rectangular wing’s flapping motion within a three-dimensional flow field using the discrete vortex method (DVM). This method is more computationally efficient because it avoids the need for generating a flow field grid at each time step, unlike the traditional simulation techniques. We evaluated the wing’s aerodynamic performance by measuring the lift and drag. The wing was subjected to a combination of chord-wise twisting and span-wise bending at varying angles of attack. In addition, a prescribed motion was imposed on the flapping wing motion. Our findings indicate that the deformable wing produces significantly more lift than a rigid wing, with only a slight increase in drag. Consequently, the lift-to-drag ratio demonstrates that deformable wings are more efficient at generating lift within a moderate angle of attack range, typically between <InlineEquation ID="IEq1"> <EquationSource Format="TEX">\( 10^\circ \)</EquationSource> <EquationSource Format="MATHML"><math> <msup> <mn>10</mn> <mo>∘</mo> </msup> </math></EquationSource> </InlineEquation> and <InlineEquation ID="IEq2"> <EquationSource Format="TEX">\( 20^\circ \)</EquationSource> <EquationSource Format="MATHML"><math> <msup> <mn>20</mn> <mo>∘</mo> </msup> </math></EquationSource> </InlineEquation>. A numerical model is employed to capture the basic wake shape and to account for more complex fluidic phenomena, such as vortex stretching. The insights from our numerical simulations are expected to provide a valuable direction for modeling the micro-air vehicles (MAVs).</p>

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Computational study of aerodynamic characteristics in flapping MAVs at different angles of attack

  • 期刊论文

  • 发表日期：

    2026年4月13日

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  • Rahul Kumar,
  • Srikant Shekhar Padhee,
  • Devranjan Samanta

摘要

In this study, we conducted numerical simulations of a rectangular wing’s flapping motion within a three-dimensional flow field using the discrete vortex method (DVM). This method is more computationally efficient because it avoids the need for generating a flow field grid at each time step, unlike the traditional simulation techniques. We evaluated the wing’s aerodynamic performance by measuring the lift and drag. The wing was subjected to a combination of chord-wise twisting and span-wise bending at varying angles of attack. In addition, a prescribed motion was imposed on the flapping wing motion. Our findings indicate that the deformable wing produces significantly more lift than a rigid wing, with only a slight increase in drag. Consequently, the lift-to-drag ratio demonstrates that deformable wings are more efficient at generating lift within a moderate angle of attack range, typically between \( 10^\circ \) 10 ∘ and \( 20^\circ \) 20 ∘ . A numerical model is employed to capture the basic wake shape and to account for more complex fluidic phenomena, such as vortex stretching. The insights from our numerical simulations are expected to provide a valuable direction for modeling the micro-air vehicles (MAVs).