Aerodynamic Study of Slotted Flap for Naca 24012 Airfoil by Dynamic Mesh Techniques and Visualization Flow

Hussein, Emad Q.; Azziz, Haider Nadhom; Rashid, Farhan Lafta

doi:10.18186/thermal.871989

Cited by 8 publications

(6 citation statements)

References 11 publications

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“…This indicates that the greater the addition of the flap angle, the more the resulting C D value will increase. This pattern is similar to the research conducted by Hussein et al [14]. This is caused by increasing the flap angle, the greater the outer cross-section which is perpendicular to the direction of airflow.…”

Section: Coefficient Of Dragsupporting

confidence: 90%

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: Coefficient Of Dragsupporting

confidence: 90%

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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“…The main concern for this study is to get the, flow visualization and determined the aerodynamic characteristics of the wing for supersonic speed. The sweep angle is varied of 0°, 20°, 40° and 60° deg, the wing has a chord length of 1𝑚 with NACA 2412 airfoils is extruding by 2.8 m. Because the wing has a symmetric geometry, so only a one half of the swept wing is needed to understand the physical phenomena of air flow at supersonic speeds, as well as flow visualization [20].…”

Section: Resultsmentioning

confidence: 99%

Sweep Angles Influence on the Aerodynamic Characteristics of NACA 2412 Wing with Supersonic Flow

Rahman¹,

Aljibory²,

Rashid³

et al. 2022

MMEP

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A sweep process of a wing is very useful technique to enhance an aircraft performance especially the aircraft which fly in the sonic and supersonic areas. In this research, the influence of swept wing on aerodynamic characteristics generation of aircraft at supersonic speeds has been studied and analyzed using CFD technique. The 3D wing model analyzed and presented in this paper of NACA 2412 profile. The governing equations such as continuity, Energy Equation, and Reynolds Averaging Never-Stokes were solved in conjunction with an analysis of dynamic meshing technique to predict the aerodynamic characteristics and pressure distribution for a wing with a sweep angle ranging from 0° to 60° and a wide range of angle of attack (AOA). In conclusion, depending on the analysis result, increasing of sweep angle can increase the ratio of lift to drag coefficient by about 15%. Moreover, the sweep angle tends to change the load distribution on wing span. Generally, the swept wing has good performance coefficient through the designing an aircraft envelope by optimizing the sweep to get an optimum value of lift/drag ratio. The efficacy and authenticity of the CFD simulations model are shown by comparing the aerodynamic properties findings from the most recent wind tunnel test.

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“…Therefore, a vortex generator is applied to the surface. In previous years, vortex generators have been studied by many experts including Kharge et al [1], Velte et al [2], Hussein et al [3] etc.…”

Section: Tonsmentioning

confidence: 99%

Experimental Study of Fluid Flow Characteristics in Wing Airfoil Naca 43018 with Parabolic Vortex Generator Using Oil Flow Visualization

Trie¹,

Hariyadi²,

Rifdian³

2023

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

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Aircraft is the science of aerodynamics that is associated with fluid flow, which is related to performance in today's aviation. One of them is technological advances in the world of aviation, namely various developments and modifications of airfoils that are carried out to delay flow separation, one of which is with a vortex generator. The flow separation event in the frictional flow on the surface of the wing (boundary Layer) can cause a stall. Therefore, by delaying the separation, the drag will be small and will get an increase in the lift force. The research study is the characteristic of fluid flow that crosses a parabolic vortex generator with the oil flow visualization method. This study aims to visually observe the fluid flow characteristics on the upper surface crossing the NACA 43018 airfoil with varying positions of the vortex generator and angle of attack (AoA). The vortex generator profile is positioned x/c = 20% from the leading edge. By using variations of Reynolds Number (Re) and angle of attack (α) on the airfoil. The freestream speed used is 20 m/s, at angles of attack (α) = 0°, 4°, 10°, 12°, 15°, and 17°. It can be proven that this research with the addition of a parabolic vortex generator increases the aerodynamic performance of the airfoil, where the aircraft from AoA 0°to 12°proves that the increasing speed of the transition to the laminar boundary layer is concluded to be a turbulent boundary layer. Based on visual experiments using a parabolic vortex generator, it shows that there is a delay in flow separation on the upper surface of NACA 43018 at an angle of attack of α = 12°to 15°.

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Aerodynamic Study of Slotted Flap for Naca 24012 Airfoil by Dynamic Mesh Techniques and Visualization Flow

Cited by 8 publications

References 11 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

Sweep Angles Influence on the Aerodynamic Characteristics of NACA 2412 Wing with Supersonic Flow

Experimental Study of Fluid Flow Characteristics in Wing Airfoil Naca 43018 with Parabolic Vortex Generator Using Oil Flow Visualization

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