Relevant bibliographies by topics / Global aerodynamic coefficients

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Global aerodynamic coefficients'

Author: Grafiati
Published: 15 June 2024
Last updated: 31 July 2025

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Journal articles on the topic "Global aerodynamic coefficients"

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Albisser, Marie, and Simona Dobre. "Sensitivity Analysis for Global Parameter Identification. Application to Aerodynamic Coefficients." IFAC-PapersOnLine 51, no. 15 (2018): 963–68. http://dx.doi.org/10.1016/j.ifacol.2018.09.069.

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Laupré, Gabriel, and Jan Skaloud. "On the Self-Calibration of Aerodynamic Coefficients in Vehicle Dynamic Model-Based Navigation." Drones 4, no. 3 (2020): 32. http://dx.doi.org/10.3390/drones4030032.

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The performance of vehicle dynamic model (VDM)-based navigation largely depends on the accurate determination of aerodynamic coefficients that are unknown a priori. Among different techniques, such as model simulations or experimental analysis in a wind tunnel, the method of self-calibration via state-space augmentation benefiting Global Navigation Satellite System (GNSS) positioning represents an interesting and economical alternative. We study this technique under simulation with the goal of determining the impact of aircraft maneuvers on the precision and (de)-correlation of the aerodynamic
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Svorcan, Jelena, Ognjen Pekovic, and Toni Ivanov. "Estimation of wind turbine blade aerodynamic performances computed using different numerical approaches." Theoretical and Applied Mechanics 45, no. 1 (2018): 53–65. http://dx.doi.org/10.2298/tam171130004s.

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Although much employed, wind energy systems still present an open, contemporary topic of many research studies. Special attention is given to precise aerodynamic modeling performed in the beginning since overall wind turbine performances directly depend on blade aerodynamic performances. Several models different in complexity and computational requirements are still widely used. Most common numerical approaches include: i) momentum balance models, ii) potential flow methods and iii) full computational fluid dynamics solutions. Short explanations, reviews and comparison of the existing computat
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Michálek, Petr, and Stanislav Hračov. "Experimental investigation of aerodynamic coefficients of the Holy Trinity Column in wind tunnel." MATEC Web of Conferences 313 (2020): 00049. http://dx.doi.org/10.1051/matecconf/202031300049.

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The analysis of the aerodynamic force coefficients of the Holy Trinity Column in Olomouc based on the experimental wind tunnel testing is presented. Two aerodynamic models corresponding to geometrical scales 1:75 and 1:150 were built using 3D-printer and tested in the smooth flow in order to define the global static wind effects. The larger model served as a reference case for the tests of the isolated column, while the model build with smaller scale enabled also the experimental examination of the influence of the closest surroundings. The comparison of the aerodynamic coefficients obtained f
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Buzica, Andrei, Lisa Debschütz, Florian Knoth, and Christian Breitsamter. "Leading-Edge Roughness Affecting Diamond-Wing Aerodynamic Characteristics." Aerospace 5, no. 3 (2018): 98. http://dx.doi.org/10.3390/aerospace5030098.

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Diamond wing configurations for low signature vehicles have been studied in recent years. Yet, despite numerous research on highly swept, sharp edged wings, little research on aerodynamics of semi-slender wings with blunt leading-edges exists. This paper reports on the stall characteristics of the AVT-183 diamond wing configuration with variation of leading-edge roughness size and Reynolds number. Wind tunnel testing applying force and surface pressure measurements are conducted and the results presented and analysed. For the investigated Reynolds number range of 2.1 × 10 6 ≤ R e ≤ 2.7 × 10 6
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Jiao, Shenghai, Ling Tao, Hao Wang, Xiao Wang, and Wenjun Ruan. "Aerodynamic Characteristics and Its Sensitivity Analysis of a Cylindrical Projectile at Different Incidences." Applied Sciences 14, no. 15 (2024): 6683. http://dx.doi.org/10.3390/app14156683.

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The accurate evaluation of aerodynamic characteristics is a prerequisite and foundation for the design of high-performance aerodynamic shapes, navigation guidance, and strength of projectiles. The nonlinearity of aerodynamic calculations for a projectile is high, and the modeling and simulation are difficult, especially under the high-angle of attack flight conditions. Small variations in flight conditions, and structural parameters, etc., may cause large deviations in aerodynamic responses. Taking a small cylindrical projectile as an example, and to realize its attitude control, it is necessa
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Zhu, Hongyu, Gang Wang, Yi Liu, and Boping Ma. "Uncertainty Analysis of Supersonic Biplane's Aerodynamic Characteristics." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 5 (2019): 909–17. http://dx.doi.org/10.1051/jnwpu/20193750909.

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Utilizing the interference of shock and expansion waves, supersonic biplane can reduce the wave drag remarkably. However, the supersonic biplane is only designed at special conditions, so that it has poor performance at off-design conditions. To analyze supersonic biplane's aerodynamic characteristics at off-design conditions, the non-instructive probabilistic collocation method has been employed to achieve uncertainty quantification. Besides, Sobol global sensitivity is adopted to accurately evaluate the influence of the input uncertainty parameters. The uncertainty parameters are Mach number
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Wiński, Krzysztof, and Adam Piechna. "Comprehensive CFD Aerodynamic Simulation of a Sport Motorcycle." Energies 15, no. 16 (2022): 5920. http://dx.doi.org/10.3390/en15165920.

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Nowadays, aerodynamics is a key focal point in the vehicle design process. Beyond its direct impact on the performance of a vehicle, it also has significant effects on economics and safety. In the last decade numerical methods, mainly Computational Fluid Dynamics (CFD), have established themselves as a reliable tool that assists in the design process and complements classical tunnel tests. However, questions remain about the possible obtained accuracy, best practices and applied turbulence models. In this paper, we present a comprehensive study of motorcycle aerodynamics using CFD methods whic
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Zalewski, Wiesław. "The Impact of Propeller on Aerodynamics of Aircraft / Wpływ Śmigła Na Aerodynamikę Samolotu." Journal of KONBiN 33, no. 1 (2015): 209–22. http://dx.doi.org/10.1515/jok-2015-0018.

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Abstract The paper presents a numerical analysis of the impact of working propellers on the aerodynamics of the aircraft. Analysis was made on the example of a twin-engined, unmanned aircraft with electric drive during the low altitude flight. Three configurations were studied and compared: the plane without propellers, the plane with pusher propellers and the plane with tractor propellers. For each configuration distributions of aerodynamic coefficients along the span of the wing and their global values for the entire aircraft were estimated. Calculations were performed using the Fluent solve
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Le-Duc, Thang, and Quoc-Hung Nguyen. "Aerodynamic Optimal Design for Horizontal Axis Wind Turbine Airfoil Using Integrated Optimization Method." International Journal of Computational Methods 16, no. 08 (2019): 1841004. http://dx.doi.org/10.1142/s0219876218410049.

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In this work, a new approach for aerodynamic optimization of horizontal axis wind turbine (HAWT) airfoil is presented. This technique combines commercial computational fluid dynamics (CFD) codes with differential evolution (DE), a reliable gradient-free global optimization method. During the optimization process, commercial CFD codes are used to evaluate aerodynamic characteristics of HAWT airfoil and an improved DE algorithm is utilized to find the optimal airfoil design. The objective of this research is to maximize the aerodynamic coefficients of HAWT airfoil at the design angle of attack (
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Dissertations / Theses on the topic "Global aerodynamic coefficients"

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Vauchel, Nicolas. "Estimation des indices de Sobol à l'aide d'un métamodèle multi-éléments : application à la dynamique du vol." Electronic Thesis or Diss., Université de Lille (2022-....), 2023. http://www.theses.fr/2023ULILN008.

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La thèse s'intéresse à une problématique concrète de sécurité des aéronefs. Le domaine de vol post-décroché est un domaine aérodynamiquement complexe où l'écoulement autour des surfaces portantes (ailes et gouvernes) peut présenter de fortes instabilités et peut être partiellement ou massivement décollé. Dans ce domaine de vol, atteignable de façon accidentelle ou volontaire (avions d'entraînement ou de voltige), les moyens de contrôle usuels sont moins efficaces, voire totalement inefficaces, ce qui peut mettre en danger le pilote et ses potentiels passagers. Le travail de recherche s'intéres
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Book chapters on the topic "Global aerodynamic coefficients"

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Eltaweel, Mahmoud, Christos Kalyvas, Yong Chen, and Mohammad Reza Herfatmanesh. "Development of a CFD Model for the Estimation of Windage Losses Inside the Narrow Air Gap of an Enclosed High-Speed Flywheel." In Springer Proceedings in Energy. Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-30960-1_16.

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AbstractConcerns over global warming and the need to reduce carbon emissions have prompted the development of novel energy recovery systems. During urban driving, a significant amount of energy is lost due to continuous braking, which can be recovered and stored. The flywheel energy storage system can efficiently recover and store the vehicle's kinetic energy during deceleration. In this study, a Computational Fluid Dynamics (CFD) model was developed to assess the impact of air gap size, and rotor cavity pressure environment on the aerodynamic performance of an enclosed non-ventilated flywheel
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Khan, Md Akhtar, and K. Vigneshwar. "Aerodynamic Analysis of Supersonic Spikes for Drag Reduction." In Global Perspectives on Robotics and Autonomous Systems. IGI Global, 2023. http://dx.doi.org/10.4018/978-1-6684-7791-5.ch006.

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This research aims to examine the flow field over a NACA 651-412 aerofoil at a supersonic Mach number (M = 2) in the presence of a sharp spike and a Hemi spherical head spike. Using a spike integrated with an aerofoil alters the flow characteristics of the aerofoil, resulting in changes in aerodynamic lift and drag. Flow visualisation graphs and coefficients of aerodynamic drag and lift are measured. In this work, two spike designs were employed: sharp edges and hemispherical edges. The flow over an aerofoil with and without a spike is also compared in order to comprehend the performance of th
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Sieliukov, Oleksandr, and Cai Licong. "CALCULATION OF THE MAIN PARAMETERS OF AN AIRCRAFT WITH A CHANNEL PROPULSION SYSTEM." In Directions for the development of science in the context of global transformations. Publishing House “Baltija Publishing”, 2025. https://doi.org/10.30525/978-9934-26-562-4-2.

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A set of basic aerodynamic parameters of an electric aircraft propulsor is proposed. An analytical method is given for determining the optimal values of design parameters, at which the maximum efficiency of the propulsor on channel fans is achieved, as well as a method for calculating parameters other than aerodynamically optimal ones, which expands the designer's possibilities for optimizing the dimensions and mass of the propulsor. The key aerodynamic parameters for the design of aircraft propulsors are emphasized. The peculiarities of considering the flight altitude at the stage of thruster
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Conference papers on the topic "Global aerodynamic coefficients"

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Bricaud, C., T. Geis, K. Dullenkopf, and H. J. Bauer. "Measurement and Analysis of Aerodynamic and Thermodynamic Losses in Pre-Swirl System Arrangements." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27191.

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In order to separately describe the dominating loss mechanisms in pre-swirled cooling air delivery systems, discharge, temperature and velocity measurements were performed for numerous designs. Whereas pre-swirl nozzles, as first component, were characterized by their discharge coefficients, total pressure losses occurring at the inlet of the receiver holes were correlated depending on the incident angle of the cooling flow. To quantify losses generated inside the rotor-stator gap, flow velocity data, acquired by means of 3D PIV, were compared to total temperature measurements. In addition the
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Bayati, Ilmas, Marco Belloli, Luca Bernini, and Alberto Zasso. "A Formulation for the Unsteady Aerodynamics of Floating Wind Turbines, With Focus on the Global System Dynamics." In ASME 2017 36th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/omae2017-61925.

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This paper proposes a formulation for the assessment of the unsteady aerodynamics of floating offshore wind turbines, based on wind tunnel experiments through surge and pitch imposed motions on the 1/75 DTU 10 MW scale model. Rotor thrust and torque were analysed out of a set of different combinations of amplitudes and frequencies of the imposed mono-harmonic motion, following the idea of splitting these forces into steady and unsteady contributions, respectively through steady and unsteady aerodynamic coefficients. The latter were analysed, for different tip-speed ratios, both experimentally
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Zhang, Chenkai, Jun Hu, Zhiqiang Wang, and Xiang Gao. "Design Work of a Compressor Stage Through High-to-Low Speed Compressor Transformation." In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3506.

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Low-speed model testing has advantages such as great accuracy, low cost and risk, so it’s widely used in the design procedure of HPC exit stage. The low-speed model testing project is conducted in Nanjing University of Aeronautics and Astronautics, to represent aerodynamic load and flow field structure of the seventh stage of a high-performance 10-stage high-pressure compressor. This paper outlines the design work of the low speed four-repeating-stage axial compressor, the third stage of which is the testing stage. The first two stages and the last stage provide the compressor with entrance an
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Hennings, H., and J. Belz. "Experimental Investigation of the Aerodynamic Stability of an Annular Compressor Cascade Performing Tuned Pitching Oscillations in Transonic Flow." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-407.

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A prerequisite for aeroelastic stability investigations on vibrating compressor cascades is the detailed knowledge of the unsteady aerodynamic loads acting on the blades. In order to obtain precise insight into the aerodynamic damping of a vibrating blade assembly, a basic experiment was performed where unsteady pressure distributions were measured for subsonic and transonic flow conditions. The experiments were performed on a non-rotating, two-dimensional section of a compressor cascade in an annular test facility. The cascade consists of 20 blades (NACA3506 profile) mounted on elastic spring
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Gaszner, Manuel, Alexander O. Pugachev, Christos Georgakis, and Paul Cooper. "Leakage and Rotordynamic Coefficients of Brush Seals With Zero Cold Clearance Used in an Arrangement With Labyrinth Fins." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94342.

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A brush-labyrinth sealing configuration consisting of two labyrinth fins upstream and one brush seal downstream is studied experimentally and theoretically. Two slightly different brush seal designs with zero cold radial clearance are considered. The sealing configurations are tested on the no-whirl and dynamic test rigs to obtain leakage performance and rotordynamic stiffness and damping coefficients. The no-whirl tests allow identification of the local rotordynamic direct and cross-coupled stiffness coefficients for a wide range of operating conditions, while the dynamic test rig is used to
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Zhang, Ao, Yan Liu, Jinguang Yang, Zhi Li, Chuang Zhang, and Yiwen Li. "Machine Learning Based Design Optimization of Centrifugal Impellers." In GPPS Xi'an21. GPPS, 2022. http://dx.doi.org/10.33737/gpps21-tc-235.

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The big data and machine learning are developing rapidly, and their applications in the aerodynamic design of centrifugal impellers and other turbomachinery have attracted wide attention. In this paper, centrifugal impellers with large flow coefficient (0.18-0.22) are taken as research objects. Firstly, through one-dimensional design and optimization, main one-dimensional geometric parameters of those centrifugal impellers are obtained. Subsequently, hundreds of samples of centrifugal impellers are obtained by using an in-house parameterization program and Latin hypercube sampling method. The
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Yang, B., Q. Xu, L. He, L. H. Zhao, Ch G. Gu, and P. Ren. "A Novel Global Optimization Algorithm and its Application to Airfoil Optimization." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25013.

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In this paper, a novel global optimization algorithm has been developed, which is named as Particle Swarm Optimization combined with Particle Generator (PSO-PG). In PSO-PG, a particle generator was introduced to iteratively generate the initial particles for PSO. Based on a series of comparable numerical experiments, it was convinced that the calculation accuracy of the new algorithm as well as its optimization efficiency was greatly improved in comparison with those of the standard PSO. It was also observed that the optimization results obtained from PSO-PG were almost independent of some cri
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Patel, Parth Y., Thannathorn Jannoi, Wenhui Zou, Vladimir Vantsevich, and Roy Koomullil. "Aerodynamic Analysis of the Utility Truck With the Morphing Boom Equipment." In ASME 2022 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/fedsm2022-88368.

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Abstract Global climate change has affected the human race for decades. As a result, severe weather changes and more substantial hurricane impact have become a typical scenario. Utility trucks with the morphing boom equipment are the first responders to access these disaster areas in bad weather conditions and restore the damages caused by the disaster. The stability of the utility trucks while driving in a heavy wind scenario is an essential aspect for the safety of the rescue crew, and aerodynamic forces caused by the wind flow constitute a significant factor that influences the stability of
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Angelini, Gino, Tommaso Bonanni, Alessandro Corsini, Giovanni Delibra, Lorenzo Tieghi, and David Volponi. "A Meta-Model for Aerodynamic Properties of a Reversible Profile in Cascade With Variable Stagger and Solidity." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76363.

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In this paper, a systematic CFD work is carried out with the aim to inspect the influence of different cascade parameters on the aerodynamic performance of a reversible fan blade profile. From the obtained results, we derive a meta-model for the aerodynamic properties of this profile. Through RANS simulations of different arrangements in cascades, the aerodynamic performance of airfoils are analyzed as Reynolds number, solidity, pitch angle and angle of attack are varied. The definition of a trial matrix allows the reduction of the minimum number of simulations required. The computed CFD value
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Ciorciari, Roberto, Ilker Kirik, and Reinhard Niehuis. "Effects of Unsteady Wakes on the Secondary Flows in the Linear T106 Turbine Cascade." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94768.

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In modern low pressure turbines the efforts to increase aerodynamic blade loading by increasing blade pitch and optimising midspan performance in order to reduce weight and complexity can produce increased losses in the endwall region. Airfoils of high flow turning and high pressure gradients between the blades generate strong secondary flows which impair the global aerodynamic performance of the blades. In addition, the unsteady incoming wakes take influence on transition phenomena on the blade surfaces and the inlet boundary layer, and consequently affect the development and the evolution of
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