Study of NACA 4412 and Selig 1223 airfoils through computational fluid dynamics

Singh, J.; Singh, Jaswinder; Singh, Ampritpal; Rana, Abhishek; Dahiya, Ajay

doi:10.14445/23488360/ijme-v2i6p104

Cited by 6 publications

(3 citation statements)

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“…Furthermore, several authors have shown that, depending on the blades’ angle of attack and their shape, the contours of static pressure and the contours of velocity magnitude around the NACA airfoil evolve. 84,85 Depending on its position and angle, these pressure differences along the blade should impact the air flows and damage caused.…”

Section: Resultsmentioning

confidence: 99%

Use of Karl Fischer titration for the localized measurement of water content in FRP composite aircraft parts removed from service

Gillet

Splawski²,

Aguirre

et al. 2023

Journal of Composite Materials

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Moisture content measurements are performed on scrapped Outlet Guide Vanes (OGV) that have operated in different climates. These measurements are made by three Karl Fischer titration methods. The results are separated into two parts. On one side, a comparison of these different techniques highlights their advantages and disadvantages. The methods for studying the samples and the duration of the tests differ. The standard method is not sufficient to extract all the water from the samples. The chemical extraction and grinding methods provide higher water content. On the other side, a mapping of the water content through three scrapped OGV blades is performed with the Karl Fischer titration. Differences are observed according to the service area climate. Concentration gradients are also visible within the part, with more water at the leading edges and less water in the foam. Parts that have flown in hot and humid regions have the lowest water contents by standard Karl Fischer titration. These measurements are compared with the analysis of the damage they have been subjected to. They allow to highlight the composite material degradation, manifested by resin erosion, which is more significant for parts that have operated in wet and humid areas. This erosion involves a lower resin percentage and could explain the lower water contents measured.

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Section: Resultsmentioning

confidence: 99%

Use of Karl Fischer titration for the localized measurement of water content in FRP composite aircraft parts removed from service

Gillet

Splawski²,

Aguirre

et al. 2023

Journal of Composite Materials

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“…NACA airfoil adalah tipe geometri airfoil yang dikembangkan oleh National Advisory Committee for Aeronautics (NACA) dengan memperhitungkan pengaruh kelengkungan surface airfoil dan penyebaran ketebalan (thickness) serta pemakaian nilai bilangan Reynold tertentu dalam pengujiannya [5]. NACA airfoil memiliki Cl dan Cd rendah dibandingkan jenis airfoil yang lain sehingga cocok untuk pesawat yang membutuhkan kecepatan tinggi dan beban yang ringan [6]. Oleh karena itu NACA banyak digunakan pada Unmanned Aerial Vehicle (UAV) [5].…”

Section: Pendahuluanunclassified

Comparison Lift and Drag of Airfoil NACA 1408 Standard and Modification Using Computational Fluid Dynamic

Usin¹,

Fernanda²,

Karudin³

et al. 2022

motivection

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An airfoil is a geometry shape of an aircraft wing designed to produce high lift force and low drag forces. Study on the air flow and pressure around of the airfoil was important step to analysis lift force and drag force. Factor affecting the lift force and drag force airfoil are the geometry and dimensions of the airfoil. This study to discus about the modification airfoil NACA 1408 was performed by adding round tip in leading edge to obtain simulate air flow by varying the angle of attack. The result showed that coefficient of lift (Cl) and coefficient of drag (Cd) was calculated from the simulations, data the highest Cl and Cd were 0.00277 and 0.00025 for the standard airfoil and for modification airfoil were 0.00343 and 0.00064. Based on the test result, the modified airfoil can produce better lift force than the standard shapes for test speed of 20 m/s. Airfoil merupakan bentuk geometri sayap pesawat terbang yang dirancang untuk menghasilkan lift force tinggi dan drag force rendah. Studi tentang aliran udara dan tekanan di sekitar airfoil adalah langkah penting untuk menganalisis lift force dan drag force. Faktor yang mempengaruhi lift force dan drag force airfoil adalah geometri dan dimensi airfoil tersebut. Penelitian ini membahas tentang modifikasi dilakukan pada airfoil NACA 1408 dengan menambahkan ujung bulat pada leading edge dan mendapatkan simulasi aliran udara dengan memvariasikan angle of attack. Hasil penelitian menunjukkan bahwa coefficient of lift dan coefficient of drag dihitung dari simulasi, data coefficient of lift dan coefficient of drag tertinggi adalah 0.00277 dan 0.00025 untuk airfoil standar dan untuk airfoil modifikasi adalah 0.00343 dan 0.00064. Berdasarkan hasil pengujian, airfoil modifikasi dapat menghasilkan lift force lebih baik daripada bentuk standar untuk kecepatan uji 20 m/s.

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“…The flowing fluid is considered as air at 20°C and the flow is steady. The boundary conditions are shown in Table 2 which are the assumptions based on the past authors' work [15,[48][49][50].…”

Section: Boundary Conditionsmentioning

confidence: 99%

Design and Analysis of Propeller for High-Altitude Search and Rescue Unmanned Aerial Vehicle

Dahal

Dura

Poudel

2021

International Journal of Aerospace Engineering

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The commercially available unmanned aerial vehicles are not good enough for search and rescue flight at high altitudes. This is because as the altitude increases, the density of air decreases which affects the thrust generation of the UAV. The objective of this research work is to design thrust optimized blade for an altitude range of 3,000–5,000 m with a density of air 0.7364 kg/m3, respectively, and perform thrust analysis. The property of aluminum alloy 1,060 being lightweight is chosen for designing and testing of blade. The blade element theory-based design and analysis code was developed, and user-friendly aerodynamic inputs were used to obtain the desired outputs. The geometry designed for an altitude range of 3,000-5,000 m faced the total stress of 6.0 MPa which was at 70% of the blade span. This stress is within the limit of yield strength of the aluminum alloy, 28 MPa. The modal analysis shows the first natural frequency occurs at around 12,000 RPM which is safe for operating the blade at 0-5,000 RPM. Experimental analysis of the blade gave a thrust of 0.92 N at 2,697 RPM at 1,400 m. The analytical solution for thrust with the same conditions was 1.7 N with 85.6% efficiency. The validation of experimental results has been done by the CFD analysis. The CFD analysis was performed in ANSYS CFX which gave a thrust value of 2.27 N for the same boundary conditions. Thus, the blade designed for high altitude SAR UAV is structurally safe to operate in 0-5,000 RPM range, and its use in search missions could save many lives in the Himalayas.

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Study of NACA 4412 and Selig 1223 airfoils through computational fluid dynamics

Cited by 6 publications

References 0 publications

Use of Karl Fischer titration for the localized measurement of water content in FRP composite aircraft parts removed from service

Use of Karl Fischer titration for the localized measurement of water content in FRP composite aircraft parts removed from service

Comparison Lift and Drag of Airfoil NACA 1408 Standard and Modification Using Computational Fluid Dynamic

Design and Analysis of Propeller for High-Altitude Search and Rescue Unmanned Aerial Vehicle

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