Analysis of the impact of trailing-edge wing flaps on the aerodynamic characteristics and performance of the Diamond DA-20 aircraft

An active lift augmentation technique combining trailing edge blowing and blown flap is explored in this study. A double-slot blown flap airfoil is designed based on NACA23015. By optimizing the configuration parameters via the neural network surrogate model and particle swarm optimization algorithm, the lift coefficient at the 8° angle of attack reaches ∼5.14, which is approximately a 24% increasement relative to the baseline single-slot blown flap airfoil. In the configuration optimization, a longer flap facilitates lower pressure on the upper airfoil surface. Additionally, the aerodynamic flap effect caused by the double-slot jet flow intensifies the lift peaks and the pressure decreases over the airfoil. Ultimately, redistributing the jet momentum to the two slots achieves a highly efficient blown flap airfoil design.

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Comparative CFD Analysis of Different Angles of Trailing-Edge Fowler Wing Flaps

Bhavsar¹,

Kartha²

2023

SAE Technical Paper Series

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<div class="section abstract"><div class="htmlview paragraph">This paper focuses on a case study to compare the performances of Fowler wing flaps that are used on the trailing edge of modern-day commercial airliners. The aim is to observe trends in coefficients of lift (C<sub>l</sub>) and drag (C<sub>d</sub>) with varying flap angles of release on a single-slotted Fowler flap and arrive at the most efficient flap configuration for flight. A series of two-dimensional analyses are carried out using computational fluid dynamics (CFD) to examine the flow separation and occurrence of stalls between the different angles of flap deflection. A two-equation, k-ω shear stress transport (SST) turbulence model is used as it helps in better prediction of flow separation and boundary layer studies. Since the study is carried out for such passenger carriers, the study focuses on the lower transonic ranges of Mach number 0.7-0.9 with a Reynolds number range of 400,000 to 500,000 considering a scaled-down model and upon taking inspiration from related literature. The flaps are analyzed at various angles of release (α) such as 0°, 15°, 25°and 50°, which are selected considering the angles that they are commonly deflected to during take-off and landing scenarios. A NACA0012 symmetrical airfoil is chosen with a fixed chord length for the wing and kept at 0° Angle of Attack (AoA) with subsequent trailing edge Fowler flaps employed for examination. A data-driven approach is followed for the investigation of characteristics represented by the different designs of the Fowler flap, thus typical lift curve plots (C<sub>l</sub> vs α), drag plots (C<sub>d</sub> vs α), and lift-to-drag ratio (C<sub>l</sub>/C<sub>d</sub>) plots (C<sub>l</sub>/C<sub>d</sub> vs α) graphs are presented to understand the comparative study. The results are discussed with respect to the data observed in the graphs and a viable conceptual configuration for the single-slotted Fowler flap is selected. This insight, research, and design have led to the development of the research paper and it is hoped that this comparative study can be used to conduct further research in the field of aeronautics.</div></div>

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Analysis of the impact of trailing-edge wing flaps on the aerodynamic characteristics and performance of the Diamond DA-20 aircraft

Cited by 3 publications

References 25 publications

Sustainable hydrogen energy in aviation – A narrative review

Sustainable hydrogen energy in aviation – A narrative review

Optimization of the double-slot blown airfoil with jet at the leading and trailing edges of the flap

Comparative CFD Analysis of Different Angles of Trailing-Edge Fowler Wing Flaps

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