Relevant bibliographies by topics / Aerodynamic calculation

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Aerodynamic calculation'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 May 2022

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Journal articles on the topic "Aerodynamic calculation"

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Дмитрій Миколайович Зінченко, Г. Ортамевзи, and А. Рахмати. "THE CALCULATION AERODYNAMIC CHARACTERISTICS OF A HYBRID AEROSTATIC AIRCRAFT." MECHANICS OF GYROSCOPIC SYSTEMS, no. 27 (October 6, 2014): 102–11. http://dx.doi.org/10.20535/0203-377127201438208.

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The article presents a justification layout a new type aircraft with two different sources lifting force – aerodynamic and aerostatic. Consider especially the exploitation aircraft easier to air, identified key issues research, unresolved tasks, formulated the task. Logged matching aerodynamic profile for bearing surface hybrid aircraft, made its adaptation. Using the method of computational aerodynamics the calculation of the flow around the bearing surface, presents an analysis of the results and conclusions and recommendations are given on an aerodynamic design.
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Wang, Jianfeng, Hao Li, Yiqun Liu, Tao Liu, and Haibo Gao. "Aerodynamic research of a racing car based on wind tunnel test and computational fluid dynamics." MATEC Web of Conferences 153 (2018): 04011. http://dx.doi.org/10.1051/matecconf/201815304011.

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Wind tunnel test and computational fluid dynamics (CFD) simulation are two main methods for the study of automotive aerodynamics. CFD simulation software solves the results in calculation by using the basic theory of aerodynamic. Calculation will inevitably lead to bias, and the wind tunnel test can effectively simulate the real driving condition, which is the most effective aerodynamics research method. This paper researches the aerodynamic characteristics of the wing of a racing car. Aerodynamic model of a racing car is established. Wind tunnel test is carried out and compared with the simulation results of computational fluid dynamics. The deviation of the two methods is small, and the accuracy of computational fluid dynamics simulation is verified. By means of CFD software simulation, the coefficients of six aerodynamic forces are fitted and the aerodynamic equations are obtained. Finally, the aerodynamic forces and torques of the racing car travel in bend are calculated.
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Ovchinnicov, V. V., and Yu V. Petrov. "THE AERODYNAMIC CHRACTERISTICS CALCULATION METHODOLOGY OF TWO-SHELL PARAGLIDERS." Civil Aviation High TECHNOLOGIES 21, no. 3 (July 3, 2018): 91–100. http://dx.doi.org/10.26467/2079-0619-2018-21-3-91-100.

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Currently, two-shell paragliders (TSP) find a sufficiently wide application, including the solution of transport problems. A two-shell paraglider is a soft wing, the form of which is supported by the high-speed pressure in the stream and it is a complex aeroelastic system. To determine the aerodynamic characteristics of such system the use of nonlinear aerodynamics and nonlinear theory of elasticity methods is required, it causes the significant computational difficulties. This paper studies the aerodynamic characteristics of various steady-state shapes of gliding parachutes, the calculation-experimental method of their calculation is proposed. It is shown that the replacement of the volumetric profile of TSP median surface allows to receive the results which correctly reflect the qualitative effects of stalled and attached flows. It leads to the assumption that such replacement was possible for obtaining data about the main patterns of parachute finite wings span flow. The aerodynamic characteristics data of TSP steady-state shapes allow to identify the regularities of their changes depending on parachute cutting shape, the deformations of its surface caused by the incoming flow or control actions. To solve the problem of gliding parachute stall, with a stream of air, the discrete vortex method with closed frameworks is used. This method allows to calculate the aerodynamic characteristics of parachutes. The middle surface airflow of TSP steady-state shape with the flow of an ideal incompressible fluid is examined. The parachute fabric permeability is not considered because the upper and lower TSP cloth is either made of low permeable or impermeable fabric. The stalled aerodynamic coefficients are determined by time averaging after calculations up to its larger values. The results of the calculations are given. The possibility of application the proposed methodology for calculation of TSP aerodynamic characteristics in the range of angles of attack to 10° and over 20° for the simplified calculation scheme with accuracy 10% is shown. At the same time, it is revealed that with the increase of soft wing elongation, it is important to consider its main surface curvature for more precise aerodynamic characteristics definition. The proposed methodology can be used for rapid assessments of aerodynamic forces at the design stage and in planning tube experiment. The obtained results can be useful in TSP design during the performance of the tube experiments.
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Bondarenko, Oleksandr, and Anton Smagliy. "Software complex for aircraft characteristics calculation." MECHANICS OF GYROSCOPIC SYSTEMS, no. 40 (December 26, 2021): 93–100. http://dx.doi.org/10.20535/0203-3771402020249156.

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The article describes the method of calculating the aerodynamic loads of the aircraft, which can be programmed within the graphic user interface. The method uses statistical data of typical aerodynamic profiles flow in wind tunnels and mathematical expressions that describe the known laws of aerohydromechanics. The graphic user interface is tested by a model of the famous Ukrainian aircraft A32 that manufactured by Aeropract company. A surface model of the aircraft for modeling consists of the theoretical surface for the wing and the fuselage. A comparison of the formula’s calculation in the graphical interface and finite element calculations is given. The software interface is built in C #.
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Yu, Jing Mei, Yan Hong Yu, and Pan Pan Liu. "Horizontal Axis Wind Turbine Numerical Simulation of Two Dimensional Angle of Attack." Advanced Materials Research 619 (December 2012): 111–14. http://dx.doi.org/10.4028/www.scientific.net/amr.619.111.

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wind power is the most effective form of wind energy utilization, modern large-scale wind turbine with horizontal axis wind mainly. Horizontal axis wind turbine aerodynamic performance calculation of the wind turbine aerodynamics research hot spot, is a wind turbine aerodynamic optimization design and calculation of critical load. Horizontal axis wind turbine airfoil aerodynamic performance of the wind turbine operation characteristics and life plays a decisive role". Using Fluent software on the horizontal axis wind turbine numerical simulation, analysis of the United States of America S809NREL airfoil aerodynamic characteristics of different angles of attack numerical simulation, analyzes the different angles of attack in the vicinity of the pressure, velocity distribution. By solving the two-dimensional unsteady, compressible N-S equations for the calculation of wind turbine airfoil S809used the characteristics of flow around. N-S equation in body-fitted coordinate system is given, with the Poisson equation method to generate the C grid.
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Shen, Kai, Hong Chen, Shi Fan Gu, and Ji Min Ni. "Research on Calculation Method of Engine Cooling Fan." Advanced Materials Research 732-733 (August 2013): 495–500. http://dx.doi.org/10.4028/www.scientific.net/amr.732-733.495.

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It’s introduced the method of calculation, modeling techniques and solution techniques of the aerodynamic performance of engine cooling fan. Based on a fan-tunnel test, the relation between static pressure, power, efficiency with volume flow is calculated in Fluent. It is proposed a few improved models and compared the calculations of different models. It’s analyzed the problems and reasons in the calculations of models and proposed the improved methods in fan test and numerical calculation. Keywords:Cooling Fan, Aerodynamic Performance, Models
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Figat, Marcin, Tomasz Goetzendorf‐Grabowski, and Zdobysław Goraj. "Aerodynamic calculation of unmanned aircraft." Aircraft Engineering and Aerospace Technology 77, no. 6 (December 2005): 467–74. http://dx.doi.org/10.1108/00022660510628453.

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Luchkov, Andrey N., Evgeny V. Zhuravlev, and Egor Y. Cheban. "METHOD OF CALCULATING THE LIFT COEFFICIENT FOR A WIG’S COMPOUND WING FLYING CLOSE TO THE GROUND." Russian Journal of Water Transport, no. 62 (March 6, 2020): 51–61. http://dx.doi.org/10.37890/jwt.vi62.39.

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In the design and characteristics justification of WIG crafts, determination of optimal aerodynamic and moment coefficients and their ratio is still one of the most important problems. Values and ratios of these coefficients provide not only technical tasks performance, but also safe operation of a WIG craft within the framework of AP standards and rules of water transport operation. The paper is devoted to the method of calculating the Cy lift coefficient for the complex compound wing with washers by using the superposition method and verification of calculated data with experimental values. The study was based on TsAGI-876 wing profile characteristics at various relative flight heights.Calculation of the aerodynamic Cy coefficient is performed in several stages:1. Calculation of the aerodynamic Cy coefficient for the center section;2. Calculation of aerodynamic Cy coefficient for the console section;3. Calculation of the total Cy coefficient by using the superposition method.The proposed method of calculation provides an accuracy of up to 93%, which can be considered a satisfactory result for preliminary design of types «B» and «C» WIG crafts.
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Guan, Xin, Hua Dong Wang, Zhi Li Sun, Xiao Guo Bi, and Xu Dong Liu. "Variation of Aerodynamic Load Engineering Analysis during Wind Turbine Run." Applied Mechanics and Materials 291-294 (February 2013): 501–6. http://dx.doi.org/10.4028/www.scientific.net/amm.291-294.501.

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In order to improve design reliability of wind turbine, it is needed that calculating method of aerodynamic load during wind turbine run. In paper from the angle of the project, NACA special airfoil of wind turbine is analyzed. Combined with thin-theory, airfoil angle of attack variation is deduced, meanwhile wind turbine actual force is calculated in each blade location point when blade of wind turbine is running based on wind shear theory and tower shadow effect. According to actual condition calculation method is engineering amplified, aerodynamic load calculation method of wind turbine blade is obtained. By this method aerodynamic load which is calculated match with experiment result, it fits better.
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Abuzov, Aleksandr, Igor' Grigor'ev, and Yaroslav Abuzov. "TO THE QUESTION OF AERODYNAMICS HULLS TRANSPORT AND CARGO AIRSHIPS DESIGNED FOR THE FOREST COMPLEX." Forestry Engineering Journal 12, no. 1 (April 15, 2022): 68–81. http://dx.doi.org/10.34220/issn.2222-7962/2022.1/6.

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The article touches upon topical issues related to the transport development of forest areas with the help of aircraft, namely aerostatic ones. An assessment of their capabilities and advantages over other modes of transport is given. Examples and technical characteristics of the developed and created experimental samples of hybrid transport-cargo airships, which were intended for operation in the forest complex, are given. The key issue that the authors consider in this article is the aerodynamics of the airship hull, which has a major impact on the movement and maneuverability of the airship in the process of carrying out transport and cargo operations. A simplified method for calculating the flow around the body of an aerostatic aircraft, which depends on the geometric parameters of the body, is presented. The main stages of calculations of aerodynamic parameters are determined, including the transverse and longitudinal flow around the hull, the movement of the aircraft with the angle of attack and the influence of aerodynamic pressure. Attention is paid to the inertial properties of the environment and, as a result, to the method of calculation when moving with acceleration, where the airship is represented by a body of revolution, which is influenced by the attached mass. The presented article is a series of scientific works of the authors aimed at studying the technical parameters of aerostatic aircraft, including aerodynamic performance
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Dissertations / Theses on the topic "Aerodynamic calculation"

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McCracken, Andrew. "Methods for the calculation of aerodynamic models for flight simulation." Thesis, University of Liverpool, 2014. http://livrepository.liverpool.ac.uk/19873/.

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Flight dynamics analysis using computational models is a key stage in the design of aircraft. The models used in industry consist of two main parts. The first is a tabular aerodynamic model which is essentially a large database of aerodynamic data. The tabular aerodynamic model is a highly dimensional database containing aerodynamic loads and moments for different parameter combinations. In order to reduce the size of the tables, a number of assumptions are made. These include having sufficient resolution of the parameter space to capture the variation in the flow dynamics; decoupling certain parameters to reduce the dimensionality; using a single dynamic derivative, assuming independence from the flow conditions; and finally neglecting flow history effects which are dominant during manoeuvres with highly unsteady flow phenomena. Secondly is the use of dynamic derivatives to simulate unsteady motion effects. These are calculated using small--amplitude forced oscillatory motions. In order to accelerate their computation, frequency domain methods are used. The Linear Frequency Domain and Harmonic Balance are two such methods used in this work. As part of the frequency domain calculations, linear solvers are used to provide solution to the frequency domain problem. These solvers use preconditioners to accelerate the time to solution. An alternative method of preconditioning is proposed in this work based on the first and second order spatial discretisation Jacobian matrices. It is shown that there is significant speed up achieved by varying the proportions of the first and second order terms in the preconditioner matrix. In order to assess the performance of the tabular models, an initial assessment is carried out using a hierarchy of manoeuvres of increasing complexity. For each test case, the replay from the tabular model is compared with the fully unsteady time--accurate CFD solution. This is in line with a framework proposed in the literature. It is shown that the tabular model performs well through the linear aerodynamic regime, although breaks down where history effects become significant. The assessment continues with a study of each of the assumptions used to formulate the tables. Again a hierarchy of test cases of increasing complexity is used. Also used are both forced and free--response manoeuvres. It is shown that the resolution and coupling assumptions have little impact on the performance of the tabular model. The use of a single dynamic derivative is not shown to have an impact either, although it is suggested that for more complicated manoeuvres, this could be important. Finally, the most significant error is introduced through neglecting history effects. It is shown that for manoeuvres where history effects dominate, such as those at the extremes of the flight envelope, the tabular model is not sufficient to effectively model the aerodynamics during these manoeuvres.
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Matouk, Rabea. "Calculation of Aerodynamic Noise of Wing Airfoils by Hybrid Methods." Doctoral thesis, Universite Libre de Bruxelles, 2016. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/240641.

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This research is situated in the field of Computational AeroAcoustics (CAA). The thesis focuses on the computation of the aerodynamic noise generated by turbulent flows around wing, fan, or propeller airfoils. The computation of the noise radiated from a device is the first step for designers to understand the acoustical characteristics and to determine the noise sources in order to modify the design toward having acoustically efficient products. As a case study, the broadband or trailing-edge noise emanating from a CD (Controlled-Diffusion) airfoil, belonging to a fan is studied. The hybrid methods of aeroacoustic are applied to simulate and predict the radiated noise. The necessary tools were researched and developed. The hybrid methods consist in two steps simulations, where the determination of the aerodynamic field is decoupled from the computation of the acoustic waves propagation to the far field, so the first part of this thesis is devoted to an aerodynamic study of the considered airfoil. In this part of the thesis, a complete aerodynamic study has been performed. Some aspects have been developed in the used in-house solver SFELES, including the implementation of a new SGS model, a new outlet boundary condition and a new transient format which is used to extract the noise sources to be exported to the acoustic solver, ACTRAN. The second part of this thesis is concerned with the aeroacoustic study where four methods have been applied, among them two are integral formulations and the two others are partial-differential equations. The first method applied is Amiet’s theory, implemented in Matlab, based on the wall-pressure spectrum extracted in a point near the trailing edge. The second method is Curle’s formulation. It is applied proposing two approaches; the first approach is the implementation of the volume and surface integrals in SFELES to be calculated simultaneously with the flow in order to avoid the storage of noise sources which requires a huge space. In the second approach, the fluctuating aerodynamic forces, already obtained during the aerodynamics simulation, are used to compute the noise considering just the surface sources. Finally, Lighthil and Möhring analogies have been applied via the acoustic solver ACTRAN using sources extracted via SFELES. Maps of the radiated noise are demonstrated for several frequencies. The refraction effects of the mean flow have been studied.
Doctorat en Sciences de l'ingénieur et technologie
info:eu-repo/semantics/nonPublished
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Faltýnek, Michal. "Aerodynamický výpočet spalinového traktu parního kotle." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417845.

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The aim of this thesis is to introduce the reader into theory, which is needed to make an aerodynamic calculation of flue gas part of steam boiler. On the back of the knowledge, project documentation and other entry parameters calculate sectional losses for each component and design a ventilator, that is suitable for our requirements.
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López, Pereira Ramón. "Validation of software for the calculation of aerodynamic coefficients : with a focus on the software package Tornado." Thesis, Linköping University, Fluid and Mechanical Engineering Systems, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-57972.

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Lopez, Pereira Ramon. "Validation of software for the calculation ofaerodynamic coefficients : with a focus on the software package Tornado." Thesis, Linköping University, Fluid and Mechanical Engineering Systems, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-58316.

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Several programs exist today for calculating aerodynamic coefficients that with some simplificationsprovide fast approximations of the values for a real aircraft.Four different programs were analyzed for this report: Tornado, AVL, PANAIR and a handbook-typepreliminary method. In addition, ANSYS CFX was used for airfoil validation. For calculation of the zerolift drag, an approximation was computed in order to calculate the remaining values that were notcalculated by the software: drag contribution for fuselages, nacelles and some horizontal stabilizersand fins.Different types of aircraft were selected for trial: two commercial aircraft (Boeing 747-100 and 777-300), a TF-8A research airplane (with area rule application: some additions were made to the fuselageto prevent large variations in the cross-section when the contribution of the wing is added), a LockheedConstellation C-69 used as a military cargo airplane, a Boeing Stratocruiser used by the USAF withtwo configurations (basic and bomber), and an Aero Commander 680 Super, similar to a Cessna 162.Two airfoils (NACA2412, 0012) were also analyzed, to investigate the limitations of software designedfor three-dimensional calculations.The accuracy of the results showed that the validity of the software depends on the planform of theaircraft, as well as the simulation parameters Mach number and Reynolds number. The shape of thewing caused some of the methods to have serious difficulties in converging to valid results, orincreased the simulation time beyond acceptable limits.


Numera finns det olika program för beräkning av de aerodynamiska koefficienterna från en modellmed vissa förenklingar som ger en snabb approximation av värdena för ett verkligt flygplan.Fyra olika program har analyserats för denna rapport: Tornado, AVL, PANAIR och en handbokbaserad preliminär metod. Dessutom användes ANSYS CFX för validering av vingprofiler . Vidberäkningen av noll-lyft motståndet, en approximation användes för de återstående delarna som inteberäknas av de andra metoderna: motståndsbidraget från flygkroppar, gondoler och vissa horisontellastabilisatorer och fenor.Olika flygplaner har testats: två trafikflygplan (Boeing 747-100 och 777-300), ett TF-8Aforskningsflygplan (med area regel användning: några tillägg gjordes på flygkroppen för att tvärsnitteninte har stora variationer när bidraget från vingen läggas), ett Lockheed Constellation C-69, ett BoeingStratocruiser som används av USAF i två konfigurationer (den vanliga och bombplan), och ett AeroCommander 680 Super, som liknar ett Cessna 162. Två vingprofiler (NACA 2412, 0012) analyseradesockså, för att kontrollera begränsningarna av programmen avsedd för tredimensionella beräkningar.Riktigheten av resultaten visade att giltigheten av programmen beror på formen av flygplanernasvingar, samt de simulationernas parametrar: Mach nummer och Reynolds nummer. Formen på vingenorsakade några av de metoderna att ha stora svårigheter med konvergensen till giltiga resultat, ellerökat simulering tid över acceptabla gränser.

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Kudela, Libor. "Aerodynamický výpocet vzduchové části parního kotle." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-319279.

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The aim of this thesis is to realize analysis of problematics of aerodynamic calculations of steam boilers on the part of combustion air. On the basis of project documentation realize evaluations of sectional dissipation factors of each component of inlet tract. Realize calculation of summary pressure (draft) loss. Specify components with highest loss and propose options of their optimization.
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Jež, Dalibor. "Využití odpadního tepla kogenerační jednotky pro výrobu technologické páry a vytápění." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232150.

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This master’s thesis deals with design of technological system for heating and process steam generation. The source of energy is a cogeneration unit. The thesis is divided into several parts. The first part is design of technological system and description. The second part is realized stoichiometric calculation and the thermal balance of steam boiler. The main part of thesis is design of the waste heat steam boiler. The thermal calculation, aerodynamic calculation, hydraulic calculation and strength calculation were made. The thesis also includes the drawing of designed waste heat steam boiler.
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Koňařík, Josef. "Analýza aerodynamiky vozidla Formule Student." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228797.

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The aim of thesis is to devise the body due to the current model in the 3D software ProEngineer and given by current Formula Student competition rules. Subsequently, the model will be created for the purposes of CFD software for numerical analysis of aerodynamics. Based on this analysis, the simulation will be obtained with the coefficient of air and axles load.
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Svoboda, Marek. "Horkovodní roštový kotel." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2019. http://www.nusl.cz/ntk/nusl-401493.

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This thesis deals with design of hot water grate boiler, where the output is water with parameters 130 °C and pressure 16 bar. In the content of the whole thesis is gradually introduced a stoichiometric calculations, which is based on the specified fuel – wood chips. This is followed by the design of the individual heating surfaces according to the thermal calculations given in the thesis. Finally, the calculation is extended by hydraulic and aerodynamic losses. Dimensional design, as a basic scheme, is shown at thesis. More detailed drawing documentation is attached to this thesis.
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Akay, Busra. "Unsteady Aerodynamic Calculations Of Flapping Wing Motion." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608773/index.pdf.

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The present thesis aims at shedding some light for future applications of &
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AVs by investigating the hovering mode of flight by flapping motion. In this study, a detailed numerical investigation is performed to investigate the effect of some geometrical parameters, such as the airfoil profile shapes, thickness and camber distributions and as well as the flapping motion kinematics on the aerodynamic force coefficients and vortex formation mechanisms at low Reynolds number. The numerical analysis tool is a DNS code using the moving grid option. Laminar Navier-Stokes computations are done for flapping motion using the prescribed kinematics in the Reynolds number range of 101-103. The flow field for flapping hover flight is investigated for elliptic profiles having thicknesses of 12%, 9% and 1% of their chord lengths and compared with those of NACA 0009, NACA 0012 and SD 7003 airfoil profiles all having chord lengths of 0.01m for numerical computations. Computed aerodynamic force coefficients are compared for these profiles having different centers of rotation and angles of attack. NACA profiles have slightly higher lift coefficients than the ellipses of the same t/c ratio. And one of the most important conclusions is that the use of elliptic and NACA profiles with 9% and 12% thicknesses do not differ much as far as the aerodynamic force coefficients is concerned for this Re number regime. Also, two different sinusoidal flapping motions are analyzed. Force coefficients and vorticity contours obtained from the experiments in the literature and present study are compared. The validation of the present computational results with the experimental results available in the literature encourages us to conclude that present numerical method can be a reliable alternative to experimental techniques.
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Books on the topic "Aerodynamic calculation"

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Raithby, G. D. Calculation of subsonic aerodynamic flows, the de Havilland Aircraft of Canada, Limited, Downsview, Ont., September 2-4, 1986. Downsview, Ont: De Havilland Aircraft of Canada, Ltd, 1986.

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Mavriplis, Dimitri J. Unstructured mesh algorithms for aerodynamic calculations. Hampton, Va: Institute for Computer Applications in Science and Engineering, 1992.

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Lan, C. Edward. Calculation of aerodynamic characteristics at high angles of attack for airplane configurations: Semi-annual status report on NASA grant NAG 1-635, August 1, 1986 - January 31, 1987. Lawrence, Kan: Flight Research Laboratory, the University of Kansas Center for Research, Inc., 1987.

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Barger, Raymond L. On minimizing the number of calculations in design-by-analysis codes. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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Ueda, Tetsuhiko. Unsteady aerodynamic calculations for general configurations by the doublet-point method. Tokyo, Japan: National Aerospace Laboratory, 1991.

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Baysal, Oktay. Navier-Stokes calculations of scramjet-nozzle-afterbody flowfields. Norfolk, Va: Dept. of Mechanical Engineering & Mechanics, College of Engineering & Technology, Old Dominion University Research Foundation, 1991.

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Baysal, Oktay. Navier-Stokes calculations of scramjet-nozzle-afterbody flowfields. Norfolk, Va: Dept. of Mechanical Engineering & Mechanics, College of Engineering & Technology, Old Dominion University Research Foundation, 1991.

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Quinn, Robert D. Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Quinn, Robert D. Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Quinn, Robert D. Real-time aerodynamic heating and surface temperature calculations for hypersonic flight simulation. Moffett Field, Calif: Ames Research Center, 1990.

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Book chapters on the topic "Aerodynamic calculation"

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Cebeci, Tuncer, and J. H. Whitelaw. "Calculation Methods for Aerodynamic Flows—a Review." In Numerical and Physical Aspects of Aerodynamic Flows III, 1–19. New York, NY: Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4926-9_1.

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Shao, Qing, Fu-ting Bao, and Chao-feng Liu. "Aerodynamic heating calculation by lattice Boltzmann equation." In Advances in Energy Science and Equipment Engineering II, 1915–22. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116174-203.

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Šafařík, P., and V. Vlček. "Using Interferometric Measurements in Calculation of Aerodynamic Forces." In Optical Methods in Dynamics of Fluids and Solids, 301–5. Berlin, Heidelberg: Springer Berlin Heidelberg, 1985. http://dx.doi.org/10.1007/978-3-642-82459-3_38.

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Ganguli, Ranjan. "Aerodynamic Derivative Calculation Using Radial Basis Function Neural Networks." In Advanced UAV Aerodynamics, Flight Stability and Control, 283–307. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118928691.ch8.

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Shmilovich, Arvin, and N. Douglas Halsey. "Calculation of Transonic Flows for Novel Engine-Airframe Installations." In Numerical and Physical Aspects of Aerodynamic Flows IV, 163–74. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-662-02643-4_10.

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Aupoix, B., S. Bonnet, C. Gleyzes, and J. Cousteix. "Calculation of Three-Dimensional Boundary Layers Including Hypersonic Flows." In Numerical and Physical Aspects of Aerodynamic Flows IV, 175–88. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-662-02643-4_11.

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Zaman, M., K. Kleineidam, L. Bakken, J. Berendt, C. Bracken, K. Butterbach-Bahl, Z. Cai, et al. "Micrometeorological Methods for Greenhouse Gas Measurement." In Measuring Emission of Agricultural Greenhouse Gases and Developing Mitigation Options using Nuclear and Related Techniques, 141–50. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-55396-8_4.

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AbstractMicrometeorological techniques are useful if greenhouse gas (GHG) emissions from larger areas (i.e. entire fields) should be integrated. The theory and the various techniques such as flux-gradient, aerodynamic, and Bowen ratio as well as Eddy correlation methods are described and discussed. Alternative methods also used are Eddy correlation, mass balance techniques, and tracer-based methods. The analytical techniques with current state-of-the-art approaches as well as the calculation procedures are presented.
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Möhlenkamp, K., and E. Fegel. "Real Time for the Calculation of the Aerodynamic of Aircrafts with Delta Wings." In Orbital Transport, 357–68. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-45720-3_27.

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Yates, E. Carson, and Robert N. Desmarais. "Calculation of Aerodynamic Sensitivities by Boundary-Integral Methods and Application to Lifting-Surface Theory." In Boundary Element Methods in Engineering, 391–97. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84238-2_48.

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Jazarević, Vladimir, and Boško Rašuo. "Numerical Calculation of Aerodynamic Noise Generated from an Aircraft in Low Mach Number Flight." In Lecture Notes in Computational Science and Engineering, 113–27. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-67202-1_9.

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Conference papers on the topic "Aerodynamic calculation"

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Ishchejkin, G. YU. "Calculation of aerodynamic forces." In SCIENCE OF RUSSIA: TARGETS AND GOALS. ЦНК МОАН, 2020. http://dx.doi.org/10.18411/sr-10-04-2020-24.

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Zielinski, Kurt A., and Jonathan Eccles. "Application of Emergent Aerodynamic Calculation Tools." In SAE World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2008. http://dx.doi.org/10.4271/2008-01-0096.

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WAN, T., and H. SARAVIA. "Aerodynamic calculation of an elliptic ring wing." In 29th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-68.

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Huang, S., and C. Béguier. "Aerodynamic Noise Calculation of a Detaching Flow." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-0080.

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Abstract A numerical study based on the macro-simulation method is carried out in order to determine the aerodynamical noise of a turbulent detaching flow. The macro-simulation method uses a Large Eddy Simulation (LES) code to obtain at the same time, the large structures of the flow and the small structures modelled by a sub-grid eddy viscosity, and an acoustic code able to calculate, in the far field, the radiated aerodynamical noises, from the Lighthill-Curle formalism. The method permits to dissociate the different aerodynamical noises: the wall noise, due to the wall-pressure fluctuations, the shear noise, due to the large scale quadrupole sources, and the turbulence self noise, generated by the small scale quadrupole sources. The case of the normal backward facing step is presented, for which the different emitted noises are analysed and compared together. Some theoretical hypotheses are also tested.
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Zeng, Xiangming, and Yihuai Hu. "Design and Aerodynamic Calculation of a Novel Sail." In 2011 Asia-Pacific Power and Energy Engineering Conference (APPEEC). IEEE, 2011. http://dx.doi.org/10.1109/appeec.2011.5749065.

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Iwase, Taku, Hideshi Obara, Hiroyasu Yoneyama, Yoshinobu Yamade, and Chisachi Kato. "Calculation of Aerodynamic Noise for Centrifugal Fan of Air-Conditioner." In ASME 2013 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/fedsm2013-16071.

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Flow fields in a centrifugal fan for an indoor unit of an air-conditioner were calculated with finite element method-based large eddy simulation (LES) with the aim of predicting fan performance and aerodynamic noise in this study. The numerical simulation code employed throughout the LES was called FrontFlow/blue (FFB). We compared 10M grid [coarse grid] and 60M grid [fine grid] calculation results for investigation of influence of grid resolution. In the fine grid, the number of grid elements in blade-to-blade direction, and of region between the shroud and the bell mouth increased in particular. By calculating with the fine grid, calculated distributions of absolute velocities at blade exit reasonably agreed with experimental results. Because of this, maximum absolute velocity by fine grid near hub decreased as compared to those by coarse grid. Calculated sound pressure level by fine grid was therefore smaller than that by coarse grid, and the overestimation of sound pressure was suppressed by calculating with fine grid. This decrease of the absolute velocity was a first factor for the improvement of calculation accuracy. Moreover, number of captured streaks on the blade, hub, and shroud surfaces by fine grid increased as compared to those by coarse grid. As a result, size of streak by fine grid became smaller than that by coarse grid. Static pressure fluctuations by fine grid on the blade, hub, and shroud surfaces therefore reduced as compared to those by coarse grid. Aerodynamic noise was related to static pressure fluctuations according to Curle’s equation. This reduction of static pressure fluctuations was therefore a second factor for improvement of calculation accuracy.
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Bhatia, Manav, and Philip S. Beran. "Adjoint-Based h-adaptive Calculation of Generalized Aerodynamic Forces." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0172.

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PARK, CHUL, and SEOKKWAN YOON. "Calculation of real-gas effects on airfoil aerodynamic characteristics." In 5th Joint Thermophysics and Heat Transfer Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1712.

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Yang, Bin, Maosong Wan, and Qinghong Sun. "Numerical calculation of aerodynamic characteristics of metro train head." In 2010 2nd International Conference on Future Computer and Communication. IEEE, 2010. http://dx.doi.org/10.1109/icfcc.2010.5497757.

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Godfrey, Andrew, and Eugene Cliff. "Direct calculation of aerodynamic force derivatives - A sensitivity-equation approach." In 36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-393.

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Reports on the topic "Aerodynamic calculation"

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MacCormack, Robert W. Magneto-Fluid Dynamics Calculations for Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, November 2007. http://dx.doi.org/10.21236/ada474960.

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Wissink, Andrew, Jude Dylan, Buvana Jayaraman, Beatrice Roget, Vinod Lakshminarayan, Jayanarayanan Sitaraman, Andrew Bauer, James Forsythe, Robert Trigg, and Nicholas Peters. New capabilities in CREATE™-AV Helios Version 11. Engineer Research and Development Center (U.S.), June 2021. http://dx.doi.org/10.21079/11681/40883.

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CREATE™-AV Helios is a high-fidelity coupled CFD/CSD infrastructure developed by the U.S. Dept. of Defense for aeromechanics predictions of rotorcraft. This paper discusses new capabilities added to Helios version 11.0. A new fast-running reduced order aerodynamics option called ROAM has been added to enable faster-turnaround analysis. ROAM is Cartesian-based, employing an actuator line model for the rotor and an immersed boundary model for the fuselage. No near-body grid generation is required and simulations are significantly faster through a combination of larger timesteps and reduced cost per step. ROAM calculations of the JVX tiltrotor configuration give a comparably accurate download prediction to traditional body-fitted calculations with Helios, at 50X less computational cost. The unsteady wake in ROAM is not as well resolved, but wake interactions may be a less critical issue for many design considerations. The second capability discussed is the addition of six-degree-of-freedom capability to model store separation. Helios calculations of a generic wing/store/pylon case with the new 6-DOF capability are found to match identically to calculations with CREATE™-AV Kestrel, a code which has been extensively validated for store separation calculations over the past decade.
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McInville, Roy M., and Frank G. Moore. A New Method for Calculating Wing Along Aerodynamics to Angle of Attack 180 deg. Fort Belvoir, VA: Defense Technical Information Center, March 1994. http://dx.doi.org/10.21236/ada277965.

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