Log in

Relevant bibliographies by topics / Aerofoil / Journal articles

To see the other types of publications on this topic, follow the link: Aerofoil.

Journal articles on the topic 'Aerofoil'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Aerofoil.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

Liang, Changping, and Huaxing Li. "Aerofoil optimization for improving the power performance of a vertical axis wind turbine using multiple streamtube model and genetic algorithm." Royal Society Open Science 5, no. 7 (2018): 180540. http://dx.doi.org/10.1098/rsos.180540.

Full text

Abstract:

This paper reports on the optimization of the NACA0015 aerofoil for improving the power performance of a vertical axis wind turbine (VAWT). The target range of the chord Re is 3 × 10 5 –10 6 , the tip speed ratio (TSR) is 2–6 and the solidity is 0.2–0.6. This aerofoil is widely applied in small-scale VAWTs. In the optimization process, in which the class and shape function transformation parametrization method was used to perturb the aerofoil geometry, the thickness and camber of the aerofoil were selected as the constraints and the value of the maximum tangential force coefficient was chosen

APA, Harvard, Vancouver, ISO, and other styles

2

Zhang, Hailang, Yu Hu, and Gengqi Wang. "The effect of aerofoil camber on cycloidal propellers." Aircraft Engineering and Aerospace Technology 90, no. 8 (2018): 1156–67. http://dx.doi.org/10.1108/aeat-08-2016-0128.

Full text

Abstract:

Purpose This paper aims to investigate the impact of aerofoil camber on the performance of micro-air-vehicle-scale cycloidal propellers. Design/methodology/approach First, experiments were conducted to validate the numerical methodology. After that, three turbulent models were compared to select the most accurate one. Then, 2D numerical simulation was carried out on 11 aerofoils with different cambers, including five cambered aerofoils, one symmetrical aerofoil and five inverse cambered aerofoils. The inverse cambered aerofoils are symmetrical about the chord line to the corresponding cambered

APA, Harvard, Vancouver, ISO, and other styles

3

Radwan M. Aljuhashy. "Numerical Study For Slotted And Vibrated Asymmetric Aerofoils." Wasit Journal of Engineering Sciences 11, no. 3 (2023): 34–44. http://dx.doi.org/10.31185/ejuow.vol11.iss3.496.

Full text

Abstract:

The aerodynamics of slotted aerofoils under various Reynolds numbers were numerically studied. Moreover, vibration of aerofoils due to the wind flow was also investigated. Different Reynolds numbers (0.25, 0.4, 0.7 and 1) ×106 were utilized using an Ansys noncommercial version. A slotted asymmetric aerofoil, which was NACA4412, was chosen to implement the concept of the current investigation. The base aerofoil was compared to an experimental study to check the number of cells above and around the aerofoil. The slotted aerofoil appeared to have more momentum on the suction side. Moreover, the s

APA, Harvard, Vancouver, ISO, and other styles

4

Shen, Xiang, Theodosios Korakianitis, and Eldad Avital. "Numerical Investigation of Surface Curvature Effects on Aerofoil Aerodynamic Performance." Applied Mechanics and Materials 798 (October 2015): 589–95. http://dx.doi.org/10.4028/www.scientific.net/amm.798.589.

Full text

Abstract:

The prescribed surface curvature distribution blade design (CIRCLE) method optimises aerofoils and blades by controlling curvature continuity and slope of curvature distribution along their surfaces. The symmetrical NACA0012 exhibits a surface curvature discontinuity at the leading edge point, and the non-symmetrical E387 exhibits slope-of-curvature discontinuities in the surface. The CIRCLE method is applied to both aerofoils to remove both surface curvature and slope-of-curvature discontinuities. Computational fluid dynamics analyses are used to investigate the curvature effects on aerodynam

APA, Harvard, Vancouver, ISO, and other styles

5

., Sundram, and Rahul Kumar. "Investigation of Airfoil Design and Analysis." International Journal for Research in Applied Science and Engineering Technology 10, no. 10 (2022): 863–80. http://dx.doi.org/10.22214/ijraset.2022.47087.

Full text

Abstract:

Abstract: In this project “Aerofoil Design and Analysis” an attempt has made to make a complete study on lift and drag coefficient of various aerofoil sections using CFD. The primary goal of this project is to learn and analyse the aerodynamic performance of wings. The objective of this study is to improve aerofoil design using the software CATIA, And Fluent Analysis using the software ANSYS. Aerofoil is a principal part of any airplane construction. How much lift force and drag force is sufficient to balance the weight of the plane is decided by the aerofoil. Aerofoils are basically divided i

APA, Harvard, Vancouver, ISO, and other styles

6

Liu, Haoji, Weicheng Di, Zixing Wei, Daochun Li, Jingwu Xiang, and Zhan Tu. "Aerodynamic optimization design of low reynolds number aerofoils based on induced laminar separation." Journal of Physics: Conference Series 2764, no. 1 (2024): 012019. http://dx.doi.org/10.1088/1742-6596/2764/1/012019.

Full text

Abstract:

Abstract At low Reynolds numbers, the design of aerofoils with a high lift-to-drag ratio (RLD) is crucial for enhancing the aerodynamic performance of Micro Air Vehicles (MAVs). However, the transition from laminar to turbulent flow plays a dominant role in the aerodynamic performance of aerofoils at Low-Reynolds-Numbers (LRN). The laminar separation bubbles formed in laminar flow alter the effective aerofoil shape, reducing aerodynamic efficiency. Additionally, predicting the shape and location of the laminar separation bubbles becomes challenging due to its sensitivity to the flight environm

APA, Harvard, Vancouver, ISO, and other styles

7

., Albi, M. Dev Anand, and G. M. Joselin Herbert. "Aerodynamic Analysis on Wind Turbine Aerofoil." International Journal of Engineering & Technology 7, no. 3.27 (2018): 456. http://dx.doi.org/10.14419/ijet.v7i3.27.17997.

Full text

Abstract:

The aerofoils of wind turbine blades have crucial influence on aerodynamic efficiency of wind turbine. There are numerous amounts of research being performed on aerofoils of wind turbines. Initially, I have done a brief literature survey on wind turbine aerofoil. This project involves the selection of a suitable aerofoil section for the proposed wind turbine blade. A comprehensive study of the aerofoil behaviour is implemented using 2D modelling. NACA 4412 aerofoil profile is considered for analysis of wind turbine blade. Geometry of this aerofoil is created using GAMBIT and CFD analysis is ca

APA, Harvard, Vancouver, ISO, and other styles

8

Zhou, Zhiyuan. "The Development and Prospect of Micro Air Vehicles." Applied and Computational Engineering 130, no. 1 (2025): 108–18. https://doi.org/10.54254/2755-2721/2025.20283.

Full text

Abstract:

This paper systematically reviews the evolution of Micro Air Vehicle (MAV) aerofoil design, covering the geometric optimization and development from fixed-wing, rotary-wing, and flapping-wing to biomimetic-wing designs. In low Reynolds number environments, there are four main types of fixed-wing aerofoils, considered the classic designs for MAVs and have significantly contributed to the future development of MAV aerofoils. Rotary-wing and flapping-wing MAVs represent the initial application of bionics in aerofoil design. At the same time, the lift mechanisms discovered in insects and birds hav

APA, Harvard, Vancouver, ISO, and other styles

9

Zachariou, E., P. Wilmott, and A. D. Fitt. "A cavitating aerofoil with a Prandtl-Batchelor eddy." Aeronautical Journal 98, no. 975 (1994): 171–76. http://dx.doi.org/10.1017/s000192400004985x.

Full text

Abstract:

Abstract A simple model is presented for an aerofoil with a recirculating Prandtl-Batchelor region behind a spoiler. Using thin aerofoil theory the model is posed as a pair of coupled nonlinear singular integrodifferential equations for the shape of the separating streamline and the distribution of vorticity along the aerofoil. These equations are solved numerically and results are presented. In particular, some conclusions are drawn regarding the lift on such aerofoils.

APA, Harvard, Vancouver, ISO, and other styles

10

Saeedi, M., F. Ajalli, and M. Mani. "A comprehensive numerical study of battle damage and repairs upon the aerodynamic characteristics of an aerofoil." Aeronautical Journal 114, no. 1158 (2010): 469–84. http://dx.doi.org/10.1017/s0001924000003961.

Full text

Abstract:

Abstract A NACA 641-412 aerofoil with circle and star damage and also three repair configurations has been numerically investigated. Two different methods of mesh generation were employed: multi structured mesh for the star damaged aerofoil and unstructured mesh for the other aerofoils. The results show that the damage will cause a reduction in lift coefficient of the aerofoil and also a different stall angle relative to that of the undamaged aerofoil. Each kind of repair improves the aerodynamic characteristics of the aerofoil considerably. The flow Field inside the damage hole and the cavity

APA, Harvard, Vancouver, ISO, and other styles

11

Campanile, L. F., and G. Thwapiah. "A non-linear theory of torsional divergence." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, no. 11 (2009): 2707–11. http://dx.doi.org/10.1243/09544062jmes1843.

Full text

Abstract:

In recent years, research on aerofoil morphing is increasingly focusing on innovative ideas such as the use of compliant systems and the exploitation of aeroelastic servo-effects. If brought to their limit, these concepts would allow operating aerofoils in aeroelastically marginally stable or even unstable conditions. In this view, a non-linear approach to aeroelastic torsional divergence becomes relevant. This article presents an extension of the well-known linear theory of divergence, which takes into account non-linear effects of structural as well as aerodynamic nature. The non-linear theo

APA, Harvard, Vancouver, ISO, and other styles

12

Haselbach, Frank, Heinz-Peter Schiffer, Manfred Horsman, Stefan Dressen, Neil Harvey, and Simon Read. "The Application of Ultra High Lift Blading in the BR715 LP Turbine." Journal of Turbomachinery 124, no. 1 (2001): 45–51. http://dx.doi.org/10.1115/1.1415737.

Full text

Abstract:

The original LP turbine of the BR715 engine featured “High Lift” blading, which achieved a 20-percent reduction in aerofoil numbers compared to blading with conventional levels of lift, reported in Cobley et al. (1997). This paper describes the design and test of a re-bladed LP turbine with new “Ultra High Lift” aerofoils, achieving a further reduction of approximately 11 percent in aerofoil count and significant reductions in turbine weight. The design is based on the successful cascade experiments of Howell et al. (2000) and Brunner et al. (2000). Unsteady wake-boundary layer interaction on

APA, Harvard, Vancouver, ISO, and other styles

13

Wibowo, Heri. "Pengaruh Sudut Serang Aerofoil Terhadap Distribusi Tekanan dan Gaya Angkat." JURNAL DINAMIKA VOKASIONAL TEKNIK MESIN 2, no. 2 (2017): 148. http://dx.doi.org/10.21831/dinamika.v2i2.15999.

Full text

Abstract:

The aerofoils are used to get the lifting force on the design of plane’s wings. The lifting force is caused by difference air velocity on upper and lower aerofoil which the magnitude depend on attack angle of aerofoil and air velocity exist surrounding. This experiment aims to show the force vector (pressure distribute) on the aerofoil. The aerofoil is attached by air with konstant velocity. The research procedure is done by change the attack angle of aerofoil on five formation. The surface of aerofoil is connected with pressure gage which disperse at 11 point of measurement. The result shows

APA, Harvard, Vancouver, ISO, and other styles

14

Baddoo, P. J., and L. J. Ayton. "Potential flow through a cascade of aerofoils: direct and inverse problems." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 474, no. 2217 (2018): 20180065. http://dx.doi.org/10.1098/rspa.2018.0065.

Full text

Abstract:

The potential flow through an infinite cascade of aerofoils is considered as both a direct and inverse problem. In each case, a perturbation expansion about a background uniform flow is assumed where the size of the perturbation is comparable to the aspect ratio of the aerofoils. This perturbation must decay far upstream and also satisfy particular edge conditions, including the Kutta condition at each trailing edge. In the direct problem, the flow field through a cascade of aerofoils of known geometry is calculated. This is solved analytically by recasting the situation as a Riemann–Hilbert p

APA, Harvard, Vancouver, ISO, and other styles

15

Sri, Ram Deepak Akella, Srinivas Baswanth Pappula Sashendra, Charan Jalli Satish, and B. S. V. Ramarao. "Aerodynamics analysis of RAF family aerofoil using computational fluid dynamics." i-manager's Journal on Mechanical Engineering 12, no. 3 (2022): 47. http://dx.doi.org/10.26634/jme.12.3.18673.

Full text

Abstract:

Aerofoil is a design that offers a gold standard ratio between the coefficient of drag to the coefficient of lift. Aerofoil are the standard cross-sectional structure of the plane wing. In this paper, a famous aerofoil family which is acknowledged to be the Royal Aircraft Factory (RAF) is regarded with all the accessible aerofoil models in that family. The pinnacle 5 aerofoils are considered and inspected for all drift editions over the viewed models with various flow transforming from 400, 420, 440, 460, 480 and 500 knots. The current research is to determine the high-quality aerofoil sketch

APA, Harvard, Vancouver, ISO, and other styles

16

Aljuhashy, et. al., Radwan M. "Evaluating the effect of unsteady air flow on a slotted aerofoil of wind turbines." Periodicals of Engineering and Natural Sciences (PEN) 11, no. 2 (2023): 197–206. https://doi.org/10.21533/pen.v11.i2.112.

Full text

Abstract:

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 atta

APA, Harvard, Vancouver, ISO, and other styles

17

Hassan, Mohd Roshdi, Yong Thian Haw, and Mohd Nasrisyam Asri. "Design Analysis of Two Ways Shape Memory Alloy (SMA) Actuated Aerofoil." Applied Mechanics and Materials 564 (June 2014): 340–45. http://dx.doi.org/10.4028/www.scientific.net/amm.564.340.

Full text

Abstract:

This paper describes the design analysis of the behavior of a shape memory alloy (SMA) plate embedded into an aerofoil. Experimentation and simulation were done to fulfill this purpose. The aerofoil is made of silicone rubber material. The SMA plate which was embedded into the maximum chamber of aerofoil during the fabrication process was measured at approximately 175mm, 63mm and 3mm in length, width and thickness respectively. Experimentation was conducted to show that the SMA plate is able to produce two-way shape memory effect. Simulation was executed by using Abaqus 6.9-1 (finite element a

APA, Harvard, Vancouver, ISO, and other styles

18

Laratro, Alex, Maziar Arjomandi, Benjamin Cazzolato, and Richard Kelso. "Self-noise of NACA 0012 and NACA 0021 aerofoils at the onset of stall." International Journal of Aeroacoustics 16, no. 3 (2017): 181–95. http://dx.doi.org/10.1177/1475472x17709929.

Full text

Abstract:

The aerodynamic noise of a NACA 0012 and NACA 0021 aerofoil is measured and compared in order to determine whether there are differences in their noise signatures with a focus on the onset of stall. Measurements of the self-noise of each aerofoil are measured in an open-jet Anechoic Wind Tunnel at Reynolds numbers of 64,000 and 96,000, at geometric angles of attack from −5° through 40° at a resolution of 1°. Further measurements are taken at Re = 96,000 at geometric angles of attack from −5 through 16° at a resolution of 0.5°. Results show that while the noise generated far into the stall regi

APA, Harvard, Vancouver, ISO, and other styles

19

Radha Krishnan, Naren Shankar, and Shiva Prasad Uppu. "A novel approach for noise prediction using Neural network trained with an efficient optimization technique." International Journal for Simulation and Multidisciplinary Design Optimization 14 (2023): 3. http://dx.doi.org/10.1051/smdo/2023002.

Full text

Abstract:

Aerofoil noise as self-noise is detrimental to system performance, in this paper NACA 0012 optimization parameters are presented for reduction in noise. Designing an aerofoil with little noise is a fundamental objective of designing an aircraft that physically and functionally meets the requirements. Aerofoil self-noise is the noise created by aerofoils interacting with their boundary layers. Using neural networks, the suggested method predicts aerofoil self-noise. For parameter optimization, the quasi-Newtonian method is utilised. The input variables, such as angle of attack and chord length,

APA, Harvard, Vancouver, ISO, and other styles

20

Abu-Abdou, K., and M. F. Zedan. "Performance of improved thin aerofoil theory for modern aerofoil sections." Aeronautical Journal 95, no. 942 (1991): 64–70. http://dx.doi.org/10.1017/s0001924000023526.

Full text

Abstract:

AbstractThe improved thin aerofoil method, which features extended expressions for lift and moment coefficients, is considered for further investigation and validation. The procedure to calculate the singularity coefficients is improved by using all aerofoil coordinates as control points in a least squares scheme. The classical NACA 0012 and NACA 65012 sections, the modern aviation aerofoil LS(1)—0417 and the extremely thick Kennedy-Marsden aerofoil are validated in place of the previously cited Karman-Trefftz aerofoil. This selection covers thickness ratios of up to 27·9%, camber ratios up to

APA, Harvard, Vancouver, ISO, and other styles

21

Koreanschi, A., O. Sugar-Gabor, and R. M. Botez. "Drag optimisation of a wing equipped with a morphing upper surface." Aeronautical Journal 120, no. 1225 (2016): 473–93. http://dx.doi.org/10.1017/aer.2016.6.

Full text

Abstract:

ABSTRACTThe drag coefficient and the laminar-to-turbulent transition for the aerofoil component of a wing model are optimised using an adaptive upper surface with two actuation points. The effects of the new shaped aerofoils on the global drag coefficient of the wing model are also studied. The aerofoil was optimised with an ‘in-house’ genetic algorithm program coupled with a cubic spline aerofoil shape reconstruction and XFoil 6.96 open-source aerodynamic solver. The wing model analysis was performed with the open-source solver XFLR5 and the 3D Panel Method was used for the aerodynamic calcul

APA, Harvard, Vancouver, ISO, and other styles

22

Chaitanya, P., P. Joseph, S. Narayanan, et al. "Performance and mechanism of sinusoidal leading edge serrations for the reduction of turbulence–aerofoil interaction noise." Journal of Fluid Mechanics 818 (April 4, 2017): 435–64. http://dx.doi.org/10.1017/jfm.2017.141.

Full text

Abstract:

This paper presents the results of a detailed experimental investigation into the effectiveness of sinusoidal leading edge serrations on aerofoils for the reduction of the noise generated by the interaction with turbulent flow. A detailed parametric study is performed to investigate the sensitivity of the noise reductions to the serration amplitude and wavelength. The study is primarily performed on flat plates in an idealized turbulent flow, which we demonstrate captures the same behaviour as when identical serrations are introduced onto three-dimensional aerofoils. The influence on the noise

APA, Harvard, Vancouver, ISO, and other styles

23

Traub, L. W. "Estimating aerofoil lift from flow angle." Aeronautical Journal 119, no. 1219 (2015): 1167–73. http://dx.doi.org/10.1017/s0001924000011180.

Full text

Abstract:

Estimation of the lift of an aerofoil is one of the fundamental measurements of fluid mechanics. Lift is commonly measured using a load cell or a force balance. Non-intrusive methods to measure lift are usually pressure based. Aerofoils may be pressure tapped where small surface orifices are connected via tubing to a pressure measurement system, either a multi-tube manometre or an electronic system. Both measurement options add cost and complication, especially in an educational setting. Pressure tapping small aerofoils can also be difficult, especially if the models are rapid prototyped (RP).

APA, Harvard, Vancouver, ISO, and other styles

24

Suddhoo, A., and I. M. Hall. "Test cases for the plane potential flow past multi-element aerofoils." Aeronautical Journal 89, no. 890 (1985): 403–14. http://dx.doi.org/10.1017/s0001924000096767.

Full text

Abstract:

SummaryThe method of images is used to calculate the analytical solution for an inviscid incompressible flow past four arbitrary circles which are then conformally mapped onto aerofoil sections. The analytical solution of the corresponding flow past the system of aerofoils is obtained and the pressure distributions about a particular three-element and a particular fourelement aerofoil are presented. These results are intended to be used to assess the accuracy of numerical methods.

APA, Harvard, Vancouver, ISO, and other styles

25

Watt, G. D., and G. V. Parkinson. "On the application of linearised theory to multi-element aerofoils Part II: Effects of thickness, camber and stagger." Aeronautical Journal 90, no. 899 (1986): 339–56. http://dx.doi.org/10.1017/s0001924000015943.

Full text

Abstract:

SummaryA linearised two-dimensional incompressible potential flow theory for two-element aerofoil sections is developed. It is capable of predicting the effects of angle of attack, flap deflection, camber, thickness, stagger and overlap of aerofoil elements on the forces. These effects are summarised in integrals which are analogous to the one-element thin aerofoil theory Munk integrals. Analytical expressions for the forces on tandem NACA 23012 aerofoils have been derived and results are presented. Comparisons are also made with a realistic slotted flap configuration with overlap for which ex

APA, Harvard, Vancouver, ISO, and other styles

26

He, W., and X. Liu. "Improved aerofoil parameterisation based on class/shape function transformation." Aeronautical Journal 123, no. 1261 (2019): 310–39. http://dx.doi.org/10.1017/aer.2018.165.

Full text

Abstract:

ABSTRACTA new aerofoil parameterisation method is put forward to represent an aerofoil by combining the leading edge modification class/shape function transformation (LEM CST) method and improved Hicks–Henne bump function’s method. The new class/shape function transformation (NEW CST) method has two additional basis functions comparing the original CST method. In order to confirm these two basis functions, the radial basis functions neural network (RBF) model is trained by some samples which are generated by the Latin hypercube design (LHD) method and Genetic Algorithm (GA) is proposed to achi

APA, Harvard, Vancouver, ISO, and other styles

27

Liu, Xiran. "Computational simulation of the Aerodynamic performance of NACA2412 and NACA25112 in low Reynolds numbers." Applied and Computational Engineering 130, no. 1 (2025): 130–39. https://doi.org/10.54254/2755-2721/2025.20317.

Full text

Abstract:

The present study introduces the basic definition of aerofoil and NACA series aerofoil. Then numerically investigates the two-dimensional aerodynamic characteristics of NACA 2412 and NACA 25112 aerofoils at a Reynolds number of 2. 0106. This study utilises the fluid dynamics simulation tool ANSYS Fluent, which is based on the finite volume method, to acquire the necessary data. The geometric model and grid of aerofoil were built with ANSYS Meshing and simulated with the pressure-based solver. In addition, the experimental environment of this study is the inlet speed of 30m/s and the air pressu

APA, Harvard, Vancouver, ISO, and other styles

28

Julius, M., S. Adio, A. Soji - Adekunle, A. Ishaq, B. Fatai, and T. Akingbade. "Unsteady aerodynamic performance of spiked and unspiked aloe vera-inspired aerofoils at low reynolds number." LAUTECH Journal of Engineering and Technology 19, no. 1 (2025): 54–64. https://doi.org/10.36108/laujet/5202.91.0150.

Full text

Abstract:

The increasing demand for Micro Aerial Vehicles (MAVs) and other low-speed aerial platforms has intensified the focus on optimizing aerofoil designs for low Reynolds number applications. This study presents a comparative analysis of the unsteady aerodynamic performance of aloe vera-inspired aerofoils, both spiked and non-spiked, at Reynolds number 1.5 × 105. By employing the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations alongside the Transition SST (four-equation) turbulence model, the research accurately characterizes the flow field and aerodynamic loads under dynamic conditions.

APA, Harvard, Vancouver, ISO, and other styles

29

Singh, Jobanpreet. "Advancements in Understanding and Mitigating Shock Wave Boundary Layer Interaction (SWBLI) Effects on Hypersonic Airfoil Performance: A Comprehensive Review." FMDB Transactions on Sustainable Energy Sequence 2, no. 2 (2024): 102–9. https://doi.org/10.69888/ftses.2024.000310.

Full text

Abstract:

Complex aerodynamic processes like Shock Wave Boundary Layer Interaction (SWBLI) affect hypersonic vehicle efficiency and safety. This comprehensive research examines SWBLI's effects on hypersonic aerofoil performance, revealing new causes and mitigating methods. This study begins with SWBLI concepts and how the boundary layer moves with flow and compression shock waves interacting with the aerofoil. We concentrate on crucial techniques for surprise wave diffraction, reflected image, and turbulent boundary layer interaction on hypersonic aerofoils. Research simulates SWBLI incidents using turb

APA, Harvard, Vancouver, ISO, and other styles

30

Raghunathan, S., T. Setoguchi, and K. Kaneko. "Predictions of Aerodynamic Performance of Wells Turbines From Aerofoil Data." Journal of Turbomachinery 112, no. 4 (1990): 792–95. http://dx.doi.org/10.1115/1.2927723.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

Zhang, Ruining. "Numerical analysis of aerodynamic performance characteristics of NACA 2412 and NACA 4412 at Re = 4000000." Applied and Computational Engineering 130, no. 1 (2025): 9–22. https://doi.org/10.54254/2755-2721/2025.20287.

Full text

Abstract:

This paper conducts a numerical analysis of the two-dimensional aerodynamic characteristics of the NACA 2412 and NACA 4412 aerofoils at a Reynolds number of Re = 4106. Employing the fluid simulation software Ansys Fluent, which is based on the finite volume method, for numerical analysis. Both the geometric model and mesh of the aerofoil are established by using Fluent Meshing, and the simulation calculation is performed based on the pressure solver. Based on the Navier-Stokes equations, the SST k- turbulence model and coupled algorithm are employed for the simulation processing. The paper sys

APA, Harvard, Vancouver, ISO, and other styles

32

Morris, Wallace J., and Zvi Rusak. "Stall onset on aerofoils at low to moderately high Reynolds number flows." Journal of Fluid Mechanics 733 (September 24, 2013): 439–72. http://dx.doi.org/10.1017/jfm.2013.440.

Full text

Abstract:

AbstractThe inception of leading-edge stall on stationary, two-dimensional, smooth, thin aerofoils at low to moderately high chord Reynolds number flows is investigated by a reduced-order, multiscale model problem via numerical simulations. The asymptotic theory demonstrates that a subsonic flow about a thin aerofoil can be described in terms of an outer region, around most of the aerofoil’s chord, and an inner region, around the nose, that asymptotically match each other. The flow in the outer region is dominated by the classical thin aerofoil theory. Scaled (magnified) coordinates and a modi

APA, Harvard, Vancouver, ISO, and other styles

33

LEPPINGTON, F. G., and R. A. SISSON. "On the interaction of a moving hollow vortex with an aerofoil, with application to sound generation." Journal of Fluid Mechanics 345 (August 25, 1997): 203–26. http://dx.doi.org/10.1017/s0022112097006253.

Full text

Abstract:

A hollow vortex in the form of a straight tube, parallel to the z-axis, and of radius a, moves in a uniform stream of fluid with velocity U in the x-direction, with U small compared with the sound speed c. This steady flow is disturbed by the presence of a thin symmetric fixed aerofoil. With a change of x-coordinate, the problem is equivalent to that of a moving aerofoil cutting through an initially fixed vortex in still fluid. The aim of this work is to determine the resulting perturbed flow, and to estimate the distant sound field. A detailed calculation is given for the perturbed velocity p

APA, Harvard, Vancouver, ISO, and other styles

34

Crowdy, Darren. "Calculating the lift on a finite stack of cylindrical aerofoils." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 462, no. 2069 (2006): 1387–407. http://dx.doi.org/10.1098/rspa.2005.1631.

Full text

Abstract:

The classic exact solution due to Lagally (Lagally, M. 1929 Die reibungslose strömung im aussengebiet zweier kreise. Z. Angew. Math. Mech . 9 , 299–305.) for streaming flow past two cylindrical aerofoils (or obstacles) is generalized to the case of an arbitrary finite number of cylindrical aerofoils. Given the geometry of the aerofoils, the speed and direction of the oncoming uniform flow and the individual round-aerofoil circulations, the complex potential associated with the flow is found in analytical form in a parametric pre-image region that can be conformally mapped to the fluid region.

APA, Harvard, Vancouver, ISO, and other styles

35

Marimuthu, Siva, and Dhavamani Chinnathambi. "Computational analysis to enhance the compressible flow over an aerofoil surface." Aircraft Engineering and Aerospace Technology 93, no. 5 (2021): 925–34. http://dx.doi.org/10.1108/aeat-06-2020-0122.

Full text

Abstract:

Purpose Since the inception of aerospace engineering, reducing drag is of eternal importance. Over the years, researchers have been trying to improve the aerodynamics of National Advisory Committee for Aeronautics (NACA) aerofoils in many ways. It is proved that smooth-surfaced NACA 0012 aerofoil produces more drag in compressible flow. Recent research on shark-skin pattern warrants a feasible solution to many fluid-engineering problems. Several attempts were made by many researchers to implement the idea of shark skin in the form of coatings, texture and more. However, those ideas are at grea

APA, Harvard, Vancouver, ISO, and other styles

36

Sharma, Shubham, Shivam Singh Tomar, and Anupam Dewan. "Impact of Aerofoil Shapes on the Performance of Darrieus Vertical Axis Turbines: A Computational Study for Offshore Wind and Hydro Applications." IOP Conference Series: Earth and Environmental Science 1411, no. 1 (2024): 012071. https://doi.org/10.1088/1755-1315/1411/1/012071.

Full text

Abstract:

Abstract An increasing energy demand, coupled with the depletion of fossil fuels and rising pollution levels, necessitates a shift towards renewable energy sources. Wind and hydro energy are a prominent renewable energy source, constituting more than 20% of the global electricity production. The objective of this study is to investigate the influence of different aerofoil shapes on the performance of Darrieus vertical axis turbine for the optimum tip speed ratio of 3.0 using Computational Fluid Dynamics (CFD) simulations. The focus is on six aerofoil profiles, namely, NACA 0012, NACA 0021, NAC

APA, Harvard, Vancouver, ISO, and other styles

37

Srinath R., Mukesh R., Inamul Hasan, and Radha Krishnan P. "Aerofoil optimization using SLSQP and validation using numerical and analytical methods." Vietnam Journal of Science and Technology 62, no. 6 (2024): 1210–26. https://doi.org/10.15625/2525-2518/19371.

Full text

Abstract:

Aircraft design optimization is one among the research enriched topic in the aerospace industry, with enhancing aircraft performance, safety, and efficiency numerous being the prime focus areas. The work done demonstrates the application of the Sequential Least Squares Programming (SLSQP) technique over a symmetrical aerofoil “NACA 0012” to improve its aerodynamic performance. The optimized aerofoil is validated using Design and Analysis Tools for Composite Aircraft (DATCOM) and Computational Fluid Dynamics (CFD) methods. The study focuses on optimizing the performance of a symmetric aerofoil,

APA, Harvard, Vancouver, ISO, and other styles

38

Marimuthu, Siva, Samer Al-Rabeei, and Hithim Ahmed Boha. "Three-Dimensional Analysis of Biomimetic Aerofoil in Transonic Flow." Biomimetics 7, no. 1 (2022): 20. http://dx.doi.org/10.3390/biomimetics7010020.

Full text

Abstract:

Since the invention of the aircraft, there has been a need for better surface design to enhance performance. This thirst has driven many aerodynamicists to develop various types of aerofoils. Most researchers have strongly assumed that smooth surfaces would be more suitable for air transport vehicles. This ideology was shattered into pieces when biomimetics was introduced. Biomimetics emphasized the roughness of a surface instead of smoothness in a fluid flow regime. In this research, the most popular 0012 aerofoils of the National Advisory Committee for Aeronautics (NACA) are considered to im

APA, Harvard, Vancouver, ISO, and other styles

39

Tang, Chengyuan. "The influence of trailing edge flaps on the aerodynamic characteristics of S1223 aerofoil." Applied and Computational Engineering 130, no. 1 (2025): 93–101. https://doi.org/10.54254/2755-2721/2025.20281.

Full text

Abstract:

The S1223 aerofoil is a low Reynolds number high lift aerofoil. Analysing the aerodynamic characteristics of this aerofoil can provide a theoretical basis for enhancing flight efficiency in the design of small unmanned aerial vehicles. This study employed the k--SST turbulence model in the fluid simulation software (ANSYS Fluent) to conduct two-dimensional numerical aerodynamic simulations on the original aerofoil and its modified versions, which included flaps (deflected 10 at 70% chord length) and slotted flaps (deflected 10 at 70% chord length with a slot width of 1.5% of the chord). The ae

APA, Harvard, Vancouver, ISO, and other styles

40

Wild, Graham. "Is that lift diagram correct? A visual study of flight education literature." Physics Education 58, no. 3 (2023): 035018. http://dx.doi.org/10.1088/1361-6552/acbad8.

Full text

Abstract:

Abstract With a complex topic such as aerodynamics, subtle points are critical. In this work images illustrating air flow around wings and aerofoils were studied to explore misunderstandings in aerodynamics education. While these images are common in textbooks and popular science media, this study was limited to the 135 physics education articles on the topic of lift, of which 49 contained illustrations of air flow around an aerofoil or wing. These 49 cases were included for qualitative comparison using visual semiotics. It was found that 28% of images did not include upwash, and only 44% incl

APA, Harvard, Vancouver, ISO, and other styles

41

Kozic, M. S., and D. Sredojevic. "Development of unstructured dynamic grids for solving unsteady two-dimensional Euler equations." Aeronautical Journal 102, no. 1014 (1998): 195–200. http://dx.doi.org/10.1017/s0001924000096305.

Full text

Abstract:

AbstractA method for the solution of the time dependent Euler equations on unstructured grids is presented for unsteady flows about oscillating aerofoils. The flow solver involves a finite volume spatial discretisation and a Runge-Kutta time-stepping scheme. A dynamic mesh algorithm is used for problems where the aerofoil moves and/or deforms. Steady and unsteady results are obtained for single and multi-element aerofoils.

APA, Harvard, Vancouver, ISO, and other styles

42

Bhatia, D., Y. Zhao, D. Yadav, and J. Wang. "Drag Reduction Using Biomimetic Sharkskin Denticles." Engineering, Technology & Applied Science Research 11, no. 5 (2021): 7665–72. http://dx.doi.org/10.48084/etasr.4347.

Full text

Abstract:

This paper explores the use of sharkskin in improving the aerodynamic performance of aerofoils. A biomimetic analysis of the sharkskin denticles was conducted and the denticles were incorporated on the surface of a 2-Dimensional (2D) NACA0012 aerofoil. The aerodynamic performance including the drag reduction rate, lift enhancement rate, and Lift to Drag (L/D) enhancement rate for sharkskin denticles were calculated at different locations along the chord line of the aerofoil and at different Angles of Attack (AOAs) through Computational Fluid Dynamics (CFD). Two different denticle orientations

APA, Harvard, Vancouver, ISO, and other styles

43

Hajian, Rozhin, and Justin W. Jaworski. "The steady aerodynamics of aerofoils with porosity gradients." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 473, no. 2205 (2017): 20170266. http://dx.doi.org/10.1098/rspa.2017.0266.

Full text

Abstract:

This theoretical study determines the aerodynamic loads on an aerofoil with a prescribed porosity distribution in a steady incompressible flow. A Darcy porosity condition on the aerofoil surface furnishes a Fredholm integral equation for the pressure distribution, which is solved exactly and generally as a Riemann–Hilbert problem provided that the porosity distribution is Hölder-continuous. The Hölder condition includes as a subset any continuously differentiable porosity distributions that may be of practical interest. This formal restriction on the analysis is examined by a class of differen

APA, Harvard, Vancouver, ISO, and other styles

44

Qin, N., Y. Zhu, and D. I. A. Poll. "Surface suction on aerofoil aerodynamic characteristics at transonic speeds." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 5 (1998): 339–51. http://dx.doi.org/10.1243/0954410981532324.

Full text

Abstract:

This paper presents a numerical study of the effects of an active flow control through surface suction on shock boundary layer interactions over transonic aerofoils. Two different aerofoils were studied. Firstly, for the purpose of validation, an NACA64A010 aerofoil with a trailing edge flap was investigated and the numerical results were compared with experimental data with and without suction for surface pressure distributions and lift and drag coefficients. Grid sensitivity has also been studied regarding the numerical accuracy. The second geometry was an RAE9647 aerofoil, which was designe

APA, Harvard, Vancouver, ISO, and other styles

45

Cameron, L., J. Early, R. McRoberts, and M. Price. "Constrained multi-objective aerofoil design using a multi-level optimisation strategy." Aeronautical Journal 119, no. 1217 (2015): 833–54. http://dx.doi.org/10.1017/s0001924000010940.

Full text

Abstract:

AbstractA novel approach for the multi-objective design optimisation of aerofoil profiles is presented. The proposed method aims to exploit the relative strengths of global and local optimisation algorithms, whilst using surrogate models to limit the number of computationally expensive CFD simulations required. The local search stage utilises a re-parameterisation scheme that increases the flexibility of the geometry description by iteratively increasing the number of design variables, enabling superior designs to be generated with minimal user intervention. Capability of the algorithm is demo

APA, Harvard, Vancouver, ISO, and other styles

46

Gong, Zhuo. "CFD Analysis of NACA2412 and NACA0012 at Low Reynolds (2.210*6) Numbers Based on ANSYS Fluent." Applied and Computational Engineering 127, no. 1 (2025): 59–67. https://doi.org/10.54254/2755-2721/2025.20218.

Full text

Abstract:

The paper is about analysing two-dimensional aerodynamic characteristics of NACA 2412 and NACA0012 aerofoils at Reynolds number of 2.210*6 using the CFD method. Numerical analysis was performed through ANSYS Fluent, a fluid simulation software based on the finite volume method. The geometry model and mesh of the aerofoil are established by ANSYS Meshing, and the simulation calculation is carried out based on the pressure solver. During simulation processing, the Spalart Almaras model is used based on the incompressible continuity equation and Navier-Stokes Equation. The aerodynamic characteris

APA, Harvard, Vancouver, ISO, and other styles

47

Lewthwaite, Matthew Thomas, and Chiemela Victor Amaechi. "Numerical Investigation of Winglet Aerodynamics and Dimple Effect of NACA 0017 Airfoil for a Freight Aircraft." Inventions 7, no. 1 (2022): 31. http://dx.doi.org/10.3390/inventions7010031.

Full text

Abstract:

Drag reduction is an ever-present challenge within the aeronautical engineering industry. This paper presents two substantial wing modifications: the addition of a winglet of a freighter aircraft and a dimpled wing on the NACA 0017 aerofoils. Studies on nine (9) different geometries of dimpled aerofoils were performed against a control model of an aerofoil without any dimple. Computational fluid dynamics (CFD) analysis was performed using two (2) commercial CFD platforms. This paper also explored two novel solutions of aircraft optimisation to mitigate the effects of drag and leading-edge pres

APA, Harvard, Vancouver, ISO, and other styles

48

Setyawan K, Catur, and Djoko Sardjadi. "PENINGKATAN KOEFISIEN GAYA ANGKAT AEROFOIL KENNEDY-MARSDEN DENGAN ZAP FLAP." Jurnal Konversi Energi dan Manufaktur 1, no. 1 (2013): 14–21. http://dx.doi.org/10.21009/jkem.1.1.2.

Full text

Abstract:

Makalah ini membahas peningkatan prestasi aerodinamika aerofoil dengan menggunakan zap flap. Penggunaan zap flap ini memungkinkan dipertahankannya bentuk asli aerofoil pada saat flap tidak digunakan. Sedangkan pada saat zap flap dijulurkan, akan terjadi peningkatan gaya angkat akibat bertambah panjangnya chord aerofoil dan berubahnya kelengkungan aerofoil. Pemakaian zap flap ini juga akan membuat aerofoil masih mempunyai sifat sebagai aerofoil satu elemen meskipun flap telah digunakan. Dengan sifat ini diharapkan penambahan gaya angkat yang diperoleh tidak akan berpengaruh banyak terhadap koef

APA, Harvard, Vancouver, ISO, and other styles

49

Ramesh, Kiran, Ashok Gopalarathnam, Kenneth Granlund, Michael V. Ol, and Jack R. Edwards. "Discrete-vortex method with novel shedding criterion for unsteady aerofoil flows with intermittent leading-edge vortex shedding." Journal of Fluid Mechanics 751 (June 23, 2014): 500–538. http://dx.doi.org/10.1017/jfm.2014.297.

Full text

Abstract:

AbstractUnsteady aerofoil flows are often characterized by leading-edge vortex (LEV) shedding. While experiments and high-order computations have contributed to our understanding of these flows, fast low-order methods are needed for engineering tasks. Classical unsteady aerofoil theories are limited to small amplitudes and attached leading-edge flows. Discrete-vortex methods that model vortex shedding from leading edges assume continuous shedding, valid only for sharp leading edges, or shedding governed by ad-hoc criteria such as a critical angle of attack, valid only for a restricted set of k

APA, Harvard, Vancouver, ISO, and other styles

50

Mohammad, Hussein K., S. M. Jali, Arz Y. Qwam Alden Qwam Alden, Viktor Kilchyk, and Bade Shrestha. "Experimental and Numerical Investigation of Channeling Effects on Noise and Aerodynamic Performance of NACA 0012 Aerofoil in Wind Turbine Applications." Renewable Energy and Power Quality Journal 21, no. 1 (2023): 373–80. http://dx.doi.org/10.24084/repqj21.328.

Full text

Abstract:

Wind power is considered one of the main sources of renewable energy in the market today. In this study, different sizes and directions of channels were created inside the NACA 0012 aerofoil, and the effect of these channels were investigated on aerodynamic noise and aerodynamic performance, experimentally and numerically. The results have shown several factors that could affect the aerodynamic noise such as flow velocity, angle of attack, and trailing edge blowing injection. The study also concluded an increase in drag coefficients and a decrease in lift coefficients for all channeled samples

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!