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<p>The aim of this paper is to develop a new numerical calculation program allowing flow control around a configuration of two adjacent airfoils including viscous drag effect. The calculation is presented by determining the effect of the shape and position of a secondary airfoil (<i>SA</i>) on the variation of the aerodynamic coefficients on a main airfoil (<i>MA</i>). Flow control depends on five independent parameters which are the chord, angle of incidence, horizontal and vertical position and geometry of <i>SA</i> relative to the leading edge of <i>MA</i>. The calculation is made by Euler method given its practical interest in the subsonic flow. The connection of all the nodes of the two airfoils together and the slip and Kutta conditions are considered to obtain a system of linear equations, where its resolution gives the distribution of the sources and the two values of the vortices. The frictional stress is subsequently determined by considering the airfoils’ boundary by adjacent flat plates. Since the airfoils’ boundary surface is given by tabulated values, the cubic spline interpolation is used to obtain an analytical equation for its upper and lower surfaces. The validation of the results is done with the case of a single airfoil by stretching the horizontal or the vertical distance between the two airfoils towards infinity. The application is made for air and for AQUILA 9.3% as <i>MA</i>, and for 5 selected airfoils as <i>SA</i>, FAUVEL 14%, RAF 30, BOEING 737, B-29, and BELL 540. The presence of the two adjacent airfoils can modify the <i>C</i><sub><i>D</i></sub>, <i>C</i><sub><i>L</i></sub>, and <i>C</i><sub><i>M</i></sub> of <i>MA</i>, respectively, up to 180.18, 42.86 and 61.06% for chosen example data compared to the values for alone <i>MA</i>.</p>

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Flow Control Around a Configuration of Two Adjacent Airfoils Including Viscous Drag Effect

  • 期刊论文

  • 发表日期：

    2026年1月26日

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  • Toufik Yahiaoui

摘要

The aim of this paper is to develop a new numerical calculation program allowing flow control around a configuration of two adjacent airfoils including viscous drag effect. The calculation is presented by determining the effect of the shape and position of a secondary airfoil (SA) on the variation of the aerodynamic coefficients on a main airfoil (MA). Flow control depends on five independent parameters which are the chord, angle of incidence, horizontal and vertical position and geometry of SA relative to the leading edge of MA. The calculation is made by Euler method given its practical interest in the subsonic flow. The connection of all the nodes of the two airfoils together and the slip and Kutta conditions are considered to obtain a system of linear equations, where its resolution gives the distribution of the sources and the two values of the vortices. The frictional stress is subsequently determined by considering the airfoils’ boundary by adjacent flat plates. Since the airfoils’ boundary surface is given by tabulated values, the cubic spline interpolation is used to obtain an analytical equation for its upper and lower surfaces. The validation of the results is done with the case of a single airfoil by stretching the horizontal or the vertical distance between the two airfoils towards infinity. The application is made for air and for AQUILA 9.3% as MA, and for 5 selected airfoils as SA, FAUVEL 14%, RAF 30, BOEING 737, B-29, and BELL 540. The presence of the two adjacent airfoils can modify the CD, CL, and CM of MA, respectively, up to 180.18, 42.86 and 61.06% for chosen example data compared to the values for alone MA.