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Investigation of aerodynamic characteristics of swept C-wing configurations at transonic speed using design of experiments and computational fluid dynamics

    Heershikesh Heerish Samputh Affiliation
    ; Lip Kean Moey Affiliation
    ; Vin Cent Tai Affiliation
    ; Yong Chai Tan Affiliation

Abstract

Authors investigated the aerodynamic characteristics of backward swept (BSCW) and forward swept (FSCW) C-wing configurations at transonic speed using Design of Experiments (DoE) and Computational Fluid Dynamics (CFD), aiming to enhance aircraft performance. Five geometric parameters for C-winglet design were identified from the literature. A quarter fractional factorial approach for the DoE was employed to analyse the effect of these parameters on aerodynamic characteristics at a constant Mach number and angle of attack of 0.8395 and 3.06°, respectively. Numerical results confirm the accuracy of the regression model in predicting aerodynamic coefficients, while normal plot highlight influential geometric parameters. Retrofitting C-winglets at the wingtips increases the aerodynamic performance by approximately 9.38% and 9.74% for BSCW and FSCW configurations respectively, compared to wings without C-winglets. The study demonstrates that utilizing a large cant angle and sweep angle of 60°, along with a low taper ratio of 0.562 for both the vertical and horizontal winglets, as well as a low cant angle of 90° for the horizontal winglet, reduces shockwave interactions on the C-winglet surface, consequently leading to a reduction in drag. It was concluded that the geometric parameters of the C-winglet play an integral role in designing new aircraft aimed at reducing drag.

Keyword : C-wing configurations, transonic speed, design of experiments, computational fluid dynamics, aerodynamic characteristics, geometric parameters

How to Cite
Samputh, H. H., Moey, L. K., Tai, V. C., & Tan, Y. C. (2024). Investigation of aerodynamic characteristics of swept C-wing configurations at transonic speed using design of experiments and computational fluid dynamics. Aviation, 28(2), 72–84. https://doi.org/10.3846/aviation.2024.21495
Published in Issue
Jun 27, 2024
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