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Dissertations / Theses on the topic 'Aerodynamic calculation'

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Published: 4 June 2021
Last updated: 5 May 2022

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1

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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2

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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3

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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4

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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5

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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6

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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8

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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9

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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10

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 &
#956
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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11

Karni, S. "Far - field boundaries and their numerical treatment." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.375917.

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12

Taylor, Dana J. "A method for the efficient calculation of elastic rotor blade dynamic response in forward flight." Diss., Georgia Institute of Technology, 1987. http://hdl.handle.net/1853/12396.

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13

Grieshaber, Michele Marie. "Interactive calculation of cross-sectional areas for aircraft design and analysis." Thesis, This resource online, 1988. http://scholar.lib.vt.edu/theses/available/etd-04272010-020357/.

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14

Gaydon, Justin Henry. "Improved panel methods for the calculation of low-speed flows around high-lift configurations." Thesis, University of Bristol, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.319082.

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15

Eleuterio, Daniel Patrick. "A comparison of bulk aerodynamic methods for calculating air-sea flux." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA359032.

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Thesis (M.S. in Meteorology and Physical Oceanography) Naval Postgraduate School, December 1998.
"December 1998." Thesis advisor(s): Qing Wang. Includes bibliographical references (p. 77-80). Also available online.
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Chiu, Yih-wan Danny. "Convergence of discrete-vortex induced-flow calculations by optimum choice of mesh." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/12390.

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17

Ok, Honam. "Development of an incomprehensible Navier-Stokes solver and its application to the calculation of separated flows /." Thesis, Connect to this title online; UW restricted, 1993. http://hdl.handle.net/1773/9969.

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18

Djayapertapa, Lesmana. "A computational method for coupled aerodynamic-structural calculations in unsteady transonic flow with active control study." Thesis, University of Bristol, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.341506.

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19

Ly, Eddie, and Eddie Ly@rmit edu au. "Numerical schemes for unsteady transonic flow calculation." RMIT University. Mathematics and Geospacial Sciences, 1999. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20081212.163408.

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An obvious reason for studying unsteady flows is the prediction of the effect of unsteady aerodynamic forces on a flight vehicle, since these effects tend to increase the likelihood of aeroelastic instabilities. This is a major concern in aerodynamic design of aircraft that operate in transonic regime, where the flows are characterised by the presence of adjacent regions of subsonic and supersonic flow, usually accompanied by weak shocks. It has been a common expectation that the numerical approach as an alternative to wind tunnel experiments would become more economical as computers became less expensive and more powerful. However even with all the expected future advances in computer technology, the cost of a numerical flutter analysis (computational aeroelasticity) for a transonic flight remains prohibitively high. Hence it is vitally important to develop an efficient, cheaper (in the sense of computational cost) and physically accurate flutter simulation tech nique which is capable of reproducing the data, which would otherwise be obtained from wind tunnel tests, at least to some acceptable engineering accuracy, and that it is essentially appropriate for industrial applications. This need motivated the present research work on exploring and developing efficient and physically accurate computational techniques for steady, unsteady and time-linearised calculations of transonic flows over an aircraft wing with moving shocks. This dissertation is subdivided into eight chapters, seven appendices and a bibliography listing all the reference materials used in the research work. The research work initially starts with a literature survey in unsteady transonic flow theory and calculations, in which emphasis is placed upon the developments in these areas in the last three decades. Chapter 3 presents the small disturbance theory for potential flows in the subsonic, transonic and supersonic regimes, including the required boundary conditions and shock jump conditions. The flow is assumed irrotational and inviscid, so that the equation of state, continuity equation and Bernoulli's equation formulated in Appendices A and B can be employed to formulate the governing fluid equation in terms of total velocity potential. Furthermore for transonic flow with free-stream Mach number close to unity, we show in Appendix C that the shocks that appear are weak enough to allow us to neglect the flow rotationality. The formulations are based on the main assumption that aerofoil slopes are everywhere small, and the flow quantities are small perturbations about their free-stream values. In Chapter 4, we developed an improved approximate factorisation algorithm that solves the two-dimensional steady subsonic small disturbance equation with nonreflecting far-field boundary conditions. The finite difference formulation for the improved algorithm is presented in Appendix D, with the description of the solver used for solving the system of difference equations described in Appendix E. The calculation of steady and unsteady nonlinear transonic flows over a realistic aerofoil are considered in Chapter 5. Numerical solution methods, based on the finite difference approach, for solving the two-dimensional steady and unsteady, general-frequency transonic small disturbance equations are presented, with the corresponding finite difference formulation described in Appendix F. The theories and solution methods for the time-linearised calculations, in the frequency and time domains, for the problem of unsteady transonic flow over a thin planar wing undergoing harmonic oscillation are presented in Chapters 6 and 7, respectively. The time-linearised calculations include the periodic shock motion via the shock jump correction procedure. This procedure corrects the solution values behind the shock, to accommodate the effect of shock motion, and consequently, the solution method will produce a more accurate time-linearised solution for supercritical flow. Appendix G presents the finite difference formulation of these time-linearised solution methods. The aim is to develop an efficient computational method for calculating oscillatory transonic aerodynamic quantities efficiently for use in flutter analyses of both two- and three-dimensional wings with lifting surfaces. Chapter 8 closes the dissertation with concluding remarks and future prospects on the current research work.
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Schoř, Pavel. "Load State of an Aircraft with an Elastic Wing." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-383528.

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V této práci je navržena metoda výpočtu zatížení letadla s netuhým křídlem, založená na spojení panelové metody prvního řádu dle Katz and Plotkin, Low-Speed Aerodynamics, 2001 s metodou stukturální analýzy dle Píštěk et al., Pevnost a životnost letadel I, 1988 a Lebofsky,Numerically Generated Tangent Stiffness Matrices for Geometrically Non-Linear Struc- tures, 2013. Panelová metoda poskytuje přasná data pro výpočet zatížení křídla od vzdušných sil za předpokladu že lze dané proudění aproximovat po- mocí potenciálního proudění, Narozdíl metod založených na interakci s CFD metodami lze navrženou metodu používat i na bežném počítači.
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Brown, T. Gordon, Timothy Vong, and Ben Topper. "CALCULATING AERODYNAMIC COEFFICIENTS FOR A NASA APOLLO BODY USING TELEMETRY DATA FROM FREE FLIGHT RANGE TESTING." International Foundation for Telemetering, 2007. http://hdl.handle.net/10150/604263.

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ITC/USA 2007 Conference Proceedings / The Forty-Third Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2007 / Riviera Hotel & Convention Center, Las Vegas, Nevada
The U.S. Army Research Laboratory (ARL) was requested by the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) to perform a free-flight experiment with a telemetry (TM) instrumented sub-scaled Apollo shaped reentry vehicle in order to determine its aerodynamic coefficients. ARL has developed a unique flight diagnostic capability for reconstructing flight trajectory and determining aerodynamic coefficients of projectiles by using sensor data telemetered from free flight experiments. A custom launch package was designed for this experiment that included the Apollo shaped projectile, which housed a modular telemetry unit, and a rapid prototyped sabot. The experiment was able to produce estimates for aerodynamic coefficients that were considered accurate and this technique is appealing to NASA for the development of their spacecraft in the future.
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Ozhamam, Murat. "Accuracy And Efficiency Improvements In Finite Difference Sensitivity Calculations." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12609128/index.pdf.

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Accuracy of the finite difference sensitivity calculations are improved by calculating the optimum finite difference interval sizes. In an aerodynamic inverse design algorithm, a compressor cascade geometry is perturbed by shape functions and finite differences sensitivity derivatives of the flow variables are calculated with respect to the base geometry flow variables. Sensitivity derivatives are used in an optimization code and a new airfoil is designed verifying given design characteristics. Accurate sensitivities are needed for optimization process. In order to find the optimum finite difference interval size, a method is investigated. Convergence error estimation techniques in iterative solutions and second derivative estimations are investigated to facilitate this method. For validation of the method, analytical sensitivity calculations of Euler equations are used and several applications are performed. Efficiency of the finite difference sensitivity calculations is improved by parallel computing. Finite difference sensitivity calculations are independent tasks in an inverse aerodynamic design algorithm and can be computed separately. Sensitivity calculations are performed on parallel processors and computing time is decreased.
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Rosolen, Célia Vanda Alves de Godoy. "Desenvolvimento analítico e numérico de perfis e cascatas Joukowski e NACA pela técnica de distribuição de vórtices." [s.n.], 2011. http://repositorio.unicamp.br/jspui/handle/REPOSIP/263330.

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Orientador: Kamal Abdel Radi Ismail
Tese (doutorado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica
Made available in DSpace on 2018-08-19T02:00:06Z (GMT). No. of bitstreams: 1 Rosolen_CeliaVandaAlvesdeGodoy_D.pdf: 6132404 bytes, checksum: 6af57a0cb75e4c1476dd73ce697ed5a5 (MD5) Previous issue date: 2011
Resumo: O presente trabalho tem como objetivos principais a elaboração de uma metodologia de cálculo de perfis e de cascatas em escoamento potencial baseado na distribuição de vórtices na superfície, o desenvolvimento de um código computacional próprio e a convalidação dos resultados obtidos. A metodologia baseia-se nos trabalhos de Martensen (1959), de Murugesan e Railly (1969) e de Lewis (1991). O comportamento aerodinâmico e os parâmetros característicos de um perfil isolado são totalmente conhecidos e existem várias técnicas analíticas e numéricas para avaliar e determinar o comportamento desses perfis. Essas técnicas analíticas podem ser estendidas para tratar os perfis experimentais como os perfis NACA com bons resultados. Neste trabalho o cálculo de perfis isolados compreende o uso do método de vórtices na superfície numa aproximação inversa. Inicialmente uma distribuição de velocidade é especificada a partir do ponto de estagnação do bordo de ataque. A distribuição de velocidade calculada sobre a superfície de um perfil inicial arbitrário é comparada com aquela requerida. A diferença entre elas é utilizada como sendo o valor de uma distribuição de vórtices que é imposta sobre o contorno. Devido ao campo desta distribuição de vórtices adicional, aparece uma distribuição de velocidades normais à superfície o que viola o conceito de linha de corrente. O contorno volta a ser uma linha de corrente quando sua inclinação local é ajustada de acordo com a razão entre os valores das velocidades normal e requerida. O perfil obtido é submetido a uma nova análise direta e a distribuição de velocidade obtida é comparada com a distribuição requerida. Os cálculos são repetidos até alcançar a convergência. O algoritmo numérico resultante foi aplicado a dois tipos de perfis, analítico (Joukowski) e experimental (NACA), para os casos de aerofólios simétrico e assimétrico. Os perfis NACA utilizados são NACA 65-010 e NACA 65-1210. Em todos os casos os perfis foram gerados usando a metodologia de distribuição de vórtices e os resultados foram comparados com os respectivos perfis originais, mostrando boa concordância. Tendo verificado que a técnica proposta e o código elaborado são válidos e produzem bons resultados, eles são aplicados à análise de cascatas de aerofólios NACA 65-1210 e de uma cascata de aerofólios de Gostelow
Abstract: This work presents a method to calculate airfoils and cascades in potential flow based upon the distribution of vortices on the profile surface, develop a computational code and validate the predictions with available well accepted results. The technique is based upon Martensen (1959), Murugesan and Railly (1969) and Lewis (1991). Cascades are usually specified according to the application and they can be stationary or moving. The aerodynamic behavior and the aerodynamic characteristics of isolated foil are known and many techniques to calculate these foils are available. These analytic techniques can be extended to handle nicely experimental foils such as the NACA's. In the present work, the method of distributing the vortices over the surface of the foil is used in the reverse sense. Initially a velocity profile is specified starting from the leading edge stagnation point. It is calculated the velocity distribution over the surface of an initial arbitrary foil and it is compared with that required. The difference between them is used as an additional distribution of vortices imposed over the surface. A distribution results in a velocity component normal to the surface and this violates the concept of the stream line. The contour turns to be a streamline when its local inclination is adopted according to the ratio of the normal velocity and the required velocity. The resultant foil is reanalyzed and the velocity distribution obtained is compared with the required distribution. The calculations are repeated until convergence is achieved. The numerical code was applied to two types of foils, analytical (Joukowski) and experimental (NACA) for the cases of symmetrical and asymmetrical foils. NACA foils used are the NACA 65-010 and NACA 65-1210. In all the cases the foils were generated using the vortex distribution technique and the resulting profiles were compared with the original profiles indicating a good agreement. These comparisons validate the proposed technique and the developed code. They were applied to analyse cascades of NACA 65-1210 foils and a cascade of the Gostelow foils
Doutorado
Termica e Fluidos
Doutor em Engenharia Mecânica
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Zuliani, Gary L. "Aerodynamic flow calculations using finite-differences and multigrid." 2004. http://link.library.utoronto.ca/eir/EIRdetail.cfm?Resources__ID=94618&T=F.

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Dignan, Jay. "Simulation of flexible aircraft using real time aerodynamic calculations." 2005. http://link.library.utoronto.ca/eir/EIRdetail.cfm?Resources__ID=370045&T=F.

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Савін, Олексій Сергійович. "Аналіз роботи котла-утилізатора тунельної печі." Магістерська робота, 2020. https://dspace.znu.edu.ua/jspui/handle/12345/2190.

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Савiн О. С. Дослідження роботи котла-утилізатора тунельної печі ВАТ «Пантелеймонівський завод вогнетривів» : кваліфікаційна робота магістра спеціальності 144 "Теплоенергетика" / наук. керівник В. І. Бахтiн. Запоріжжя : ЗНУ, 2020. 86 с.
UA : Робота викладена на 86 сторінок друкованого тексту, містить 7 таблиць, 8 рисунків. Перелік посилань включає 28 джерел з них на іноземній мові 5. В магістерській роботі вирішено актуальну науково - технічну задачу підвищення енергетичної ефективності промислового обладнання – тунельної печі шляхом використання теплових вторинних енергетичних ресурсів
EN : The work is presented on 86 pages of printed text, contains 7 tables, 8 figures. The list of references includes 28 sources, 5 of them in foreign language. The master 's work solved the actual scientific and technical problem of increasing the energy efficiency of industrial equipment - tunnel kiln by using thermal secondary energy resources
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27

Тимчук, Ірина Сергіївна. "Проект системи очистки газів, що утворюються при конвертерному виробництві конструкційних сталей." Магістерська робота, 2020. https://dspace.znu.edu.ua/jspui/handle/12345/5050.

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Abstract:
Тимчук І. С. Проект системи очистки газів, що утворюються при конвертерному виробництві конструкційних сталей : кваліфікаційна робота магістра спеціальністі 183 "Технологія захисту навколишнього середовища" / наук. керівник Г. Б. Кожемякін. Запоріжжя : ЗНУ. 2020. 92 с.
UA : Виконаний аналіз існуючих технологій очищення газів киснево-конвертерного виробництва. Проведено розрахунки, за результатом яких було підібрано технологічне обладнання – апарати для очищення технологічного газу. Виконано розрахунок аеродинамічного тракту,було підібрано тягодуттєвий пристрій. Обрано апарати для утилізації газу та вловленого пилу.
EN : The analysis of existing technologies for cleaning gases by BOF production has been carried out.Сalculations for selection of process equipment for gas process cleaning has been implemented. Aerodynamic route calculation has been made, draft consummation has been selected. Equipment for gas recovery and captured dust has been selected.
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