Aerodynamic characteristics of airfoil with single plain flap for light airplane wing

Todorov, Milcho

doi:10.1109/miltechs.2015.7153648

Cited by 5 publications

(4 citation statements)

References 10 publications

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“…The simulation process can be divided into three parts, namely: Pre-processing, processing, and post-processing. The test object uses a Cessna C208b Grand Caravan wing with dimensions of 1:1 to the actual dimensions and flap geometry based on Todorov's research [8] so that the results obtained can be validated.…”

Section: Methodsmentioning

confidence: 99%

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Numerical Simulation of Effect Modification of Single Slotted Flap on Wing Cessna C208B Grand Caravan for Aerodynamic Performance

Yusuf¹,

Hariyadi²,

Pambudiyatno³

2023

Proceedings of the International Conference on Advance Transportation, Engineering, and Applied Science (ICATEAS 2022)

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A wing through which fluid flows will form a three-dimensional separation caused by two interacting boundary layers. This separation will result in secondary flow which can be detrimental to airfoil performance. Until now, aircraft often use a slotted type flap that can prevent separation so that it can reduce the value of less resistance. This study will examine the performance and aerodynamic characteristics of the modified single-slotted flap on the Cessna 208b Grand Caravan wing. The method used is a numerical simulation with CFD software in the form of ANSYS. The test object is a modified Cessna 208b Grand Caravan wing with a single slotted flap with a flap angle (α F ) of 0°, 15°, and 30°to determine the effect of aerodynamic performance. The angles of attack reviewed are α = 0°, 2°, 4°, 6°, 8°, 10°, 12°, 14°, 15°, 16°, 18°, and 20°. The fluid flow used is air with a cruising speed of 96 m/s above sea level in stable conditions. The simulation results show that the addition of flap angle modification on the Cessna C208b Grand Caravan wing can affect both performance and aerodynamic characteristics. At a speed of 96 m/s, increasing the flap angle can decrease the value of C L /C D at high angles of attack. However, the addition of the flap angle can provide a better C L /C D value at low angles of attack.

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Section: Methodsmentioning

confidence: 99%

“…Some experts who have examined the dynamics of fluid flow in slotted flaps include Kasim [3], Chapman [4], Foster [5], Velkova [6,7], and others. Todorov [8] conducted research single slotted flaps for light airplane wings. The method that will be used in this study is a two-dimensional numerical simulation using fluent software.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Effect Modification of Single Slotted Flap on Wing Cessna C208B Grand Caravan for Aerodynamic Performance

Yusuf¹,

Hariyadi²,

Pambudiyatno³

2023

Proceedings of the International Conference on Advance Transportation, Engineering, and Applied Science (ICATEAS 2022)

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“…Wenzinger [9] tested various flap types in a wind tunnel, with the slotted flap showing one of the largest increases in C L . Todorov [10] and Hussein et al [11] found increased C L and C D values in simulations by modifying airfoils with a slotted flap. Prabhakar and Ohri [12] found good agreement in C L between their 3D simulation of a plain NACA 2412 and wind tunnel data from Saha [13]; they did not compare their 3D model to a 2D one.…”

Section: Introductionmentioning

confidence: 98%

NumericalStudy of Turbulent Flows over a NACA 0012 Airfoil: Insights into Its Performance and the Addition of a Slotted Flap

Steenwijk,

Druetta

2023

Applied Sciences

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This work provides a comprehensive overview of various aspects of airfoil CFD simulations. The airflow around a 2D NACA 0012 airfoil at various angles of attack is simulated using the RANS SST turbulent flow model and compared to experimental data. The airfoil is then modified with a slotted flap and additionally the angle of the flap is altered. The flow model is subsequently coupled to a heat transfer model to compare the isothermal versus non-isothermal performance. The airfoil with the slotted flap shows increased CL and CD values compared to the standard NACA 0012. Larger flap angles further increase the CL and CD. The lift and drag coefficients show no difference in the non-isothermal model compared to the isothermal model, indicating the isothermal model is sufficient for this system. The 3D model without wingtips shows a similar CL to the 2D model as it effectively has an infinite span. Adding a wingtip reduces the lift coefficient, as the air can flow around the wingtip, increasing the pressure on top of the wing. Overall, these results match the behavior expected from wing theory well, showing how CFD can be effectively applied in the development and optimization of wings, flaps, and wingtips.

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“…A numerical analysis was conducted by Michael Todorov [16] concluded that the slotted wing had more significant lift force than that from the normal wing. The unsteady wind flow around a symmetric aerofoil was conducted numerically by Kurtulus [17].…”

Section: Introductionmentioning

confidence: 99%

Evaluating the effect of unsteady air flow on a slotted aerofoil of wind turbines

Aljuhashy¹,

Al-Bakri²,

Alrubaiy³

2023

PEN

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In this study, three types of aerofoils were examined at various angles of attack and at a steady value then fluctuated of air flow. Then, the findings were compared to the XFOIL prediction results. The experimental and simulation results were consistent to some extent with the XFOIL prediction results. The shape of the chosen aerofoils was modified by making a slot through the blade the aerofoil and studying their effect on the aerodynamics of the modified shape. The slotted aerofoil shape was studied as it faced a fluctuated wind flow. The results revealed that the increase in angles of attack, the lift force increased and approximated its maximum value and then began to decrease with the slot. During the calculations, a case study for the number of elements was done to obtain the best mesh.The experimental and simulations were conducted by using ANSYS CFD at Reynolds number 10 6 and AOA equals (0°, 4°, 8°, 10°, 12°, 15°, 16°, 17°, 18°) for three shapes of aerofoils which are without a slot, two of which are symmetrical, NACA 0012 and NACA 0015, and one asymmetrical, which is NACA 4415. The slotted aerofoil (existence of an opening after 40% from the leading edge) which is the NACA 0015 aerofoil, was simulated.

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Aerodynamic characteristics of airfoil with single plain flap for light airplane wing

Cited by 5 publications

References 10 publications

Numerical Simulation of Effect Modification of Single Slotted Flap on Wing Cessna C208B Grand Caravan for Aerodynamic Performance

Numerical Simulation of Effect Modification of Single Slotted Flap on Wing Cessna C208B Grand Caravan for Aerodynamic Performance

NumericalStudy of Turbulent Flows over a NACA 0012 Airfoil: Insights into Its Performance and the Addition of a Slotted Flap

Evaluating the effect of unsteady air flow on a slotted aerofoil of wind turbines

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