. "Aerodynamics"@en . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . "Fundamentals of experimental aerodynamics"@en . . "3" . "Not provided" . . "Presential"@en . "FALSE" . . "aerodynamics and fluid modelling"@en . . "6" . "no data" . . "Presential"@en . "TRUE" . . "Aerodynamics"@en . . "3" . "Introduction to aerodynamics, aerodynamic objectives and re-\nsearch methods in aerodynamics. Airfoil theory: description of ge-\nometry, pressure distribution over the airfoil, aerodynamic force co-\nefficients, airfoil aerodynamic characteristics. Finite extension air-\nfoil: description of geometry, rotary lifting line theory, induced drag,\nairfoil aerodynamic characteristics. Subcritical and supercritical air-\nfoil and wing flow. Elements of high speed aerodynamic theory:\nsmall disturbance theory, sound barrier, densification and dilution\nwaves, aerodynamic heating. Aerodynamic interference, super-\nsonic air flow, elements of complete aircraft aerodynamics, experi-\nmental aerodynamic characteristics of model aircraft." . . "Presential"@en . "FALSE" . . "Aeroelasticity"@en . . "2" . "General knowledge of aerodynamics of non-stationary flow, main\nequations, Lagrange integral, velocity potential, boundary condi-\ntions, aerodynamic effects of circulationless and circulatory flow.\nFlow of a thin airfoil with finite velocity at the flow edge. Effect of\nwing haunch. Flatter, equations of motion, flexion-torsion flatter of\nwing airfoil. Influence of geometric, elastic and mass characteristics\non critical flatter velocity. Flex-torsional flatter of a finite span wing,\nequations of equilibrium. Approximate methods for calculating flat-\nter velocity and frequency. Galerkin method. Criteria of elastic sta-\nbility of a structure in flow. Wing flatter oblique wing. Low elongation\nwing flatter. Flatter of the tailplane. Flatter with one degree of free-\ndom. Flatter free-from-attachment aircraft. Flatter of plates and\nshells. Non-linear flatter issues. Detachment Flatter. Static aeroe-\nlasticity problems. Flatter research from historical perspective." . . "Presential"@en . "FALSE" . . "Aeroelasticity"@en . . "2" . "General knowledge of aerodynamics of non-stationary flow, main\nequations, Lagrange integral, velocity potential, boundary condi-\ntions, aerodynamic effects of circulationless and circulatory flow.\nFlow of a thin airfoil with finite velocity at the flow edge. Effect of\nwing haunch. Flatter, equations of motion, flexion-torsion flatter of\nwing airfoil. Influence of geometric, elastic and mass characteristics\non critical flatter velocity. Flex-torsional flatter of a finite span wing,\nequations of equilibrium. Approximate methods for calculating flat-\nter velocity and frequency. Galerkin method. Criteria of elastic sta-\nbility of a structure in flow. Wing flatter oblique wing. Low elongation\nwing flatter. Flatter of the tailplane. Flatter with one degree of free-\ndom. Flatter free-from-attachment aircraft. Flatter of plates and\nshells. Non-linear flatter issues. Detachment Flatter. Static aeroe-\nlasticity problems. Flatter research from historical perspective." . . "Presential"@en . "FALSE" . . "Fundamentals of experimental aerodynamics"@en . . "3" . "no data" . . "Presential"@en . "FALSE" . . "Aerodynamics and cfd"@en . . "no data" . "This module provides introduction to the fundamental principles of aerodynamics and development of experimental laboratorial procedures for basic aerodynamics. Students learn basic concepts of Computational Fluid Dynamics (CFD) to be used in aerodynamics problems." . . "Presential"@en . "TRUE" . . "Applied aerodynamics"@en . . "no data" . "This module introduces more advanced concepts of aerodynamics to develop further aircraft wing aerodynamics and Computational Fluid Dynamics (CFD) for the solution of aerodynamic problems. It will provide a flight test experience to students." . . "Presential"@en . "TRUE" . . "Aerodynamics 1"@en . . "2" . "Good knowledge of the fundamental concepts and principles of the Aerodynamics of airplane" . . "Presential"@en . "TRUE" . . "Aerodynamics of continuous and rarefied flows"@en . . "6" . "General introduction. Physical properties of the atmosphere, the upper atmosphere. Fundamentals of thermodynamics. \r\nAerodynamic forces and moments acting on a missile. Drag force, spin damping moment, lift and normal forces, \r\noverturning moment, Magnus force and moment, pitch damping force and moment." . . "Presential"@en . "FALSE" . . "Fundamental aerodynamics"@en . . "7.50" . "NA" . . "Presential"@en . "TRUE" . . "Further aerodynamics"@en . . "7.50" . "NA" . . "Presential"@en . "FALSE" . . "Advanced aerodynamics"@en . . "7.50" . "NA" . . "Presential"@en . "FALSE" . . "Aeroelasticity"@en . . "7.50" . "NA" . . "Presential"@en . "FALSE" . . "Aerodynamics"@en . . "10.00" . "Unit Information\nHigh speed flows and the effects of compressibility, fundamental ideas of aerofoil and wing theory, potential models for aerofoils and wings, introduction to helicopter aerodynamics.\n\nAims:\n\nTo establish a basic understanding of fluid flows related to fixed and rotary wing aircraft. To provide fundamental tools and concepts required for experimental, theoretical and computational modelling.\n\nYour learning on this unit\nUpon successful completion of this unit, the student will be able to:\n\nexplain the various levels of approximation used in aerodynamic modelling, and state the limitations of each model;\napply 2D incompressible, inviscid theory to model the flow around simple bodies and aerofoils, in particular using thin aerofoil theory and panel methods;\napply 3D incompressible, inviscid theory to model the flow around finite wings, and to explain the effect of planform on aerodynamic behaviour and on the generation of lift-dependent drag;\nuse basic compressible flow theory to model simple 1D and 2D flows, and explain the impact of compressibility on intake and nozzle flows and on wing characteristics;\napply simple fluid mechanics models to the aerodynamic design of rotary wing aircraft;\ntake part in aerodynamics experiments and analyse and interpret collected data" . . "Presential"@en . "TRUE" . . "Numerical and simulation methods for aerodynamics"@en . . "5.00" . "Unit Information\nThis unit is an introduction to the fundamental mathematical and physical principles involved in the development and application of modern methods in numerical and simulation methods for aerodynamics. Forms of the governing flow equations are first discussed and these are then reduced to a simple model equation, which is used for the development and testing of fundamental numerical methods. Accuracy, stability and convergence of these schemes are investigated mathematically. Issues involves in applying these methods to real aerodynamic flows are the discussed, i.e. methods required to produce simulation methods, including mesh generation aspects, finite-volume methods, data storage and memory implications, and the impact of continuing developments in computer architecture.\n\nAims:\n\nThe aim of this unit is to equip the student with:\n\nKnowledge and understanding of the fundamental mathematical and physical principles involved in the development of numerical methods;\n\nKnowledge and understanding of the issues involved in applying modern numerical methods in computational aerodynamics;\n\nKnowledge and understanding of methods of mesh generation and links with numerical code development;\n\nKnowledge and understanding of the impact of developments in computer hardware and software on application of computational methods;\n\nSkills necessary to develop numerical simulation codes." . . "Presential"@en . "TRUE" . . "Experimental methods for aerodynamics and aeroacoustics"@en . . "10.00" . "An overview of content\nThis unit embarks the students on a journey of defining and studying a fundamental aerodynamic problem of interest with advanced measurement techniques (microphone, pressure sensor, hot-wire anemometry and laser flow diagnostics), executed in the wind tunnel facilities. Through the learning journey, the students will: be introduced major types of aerodynamic and aeroacoustics test facilities; be exposed to different measurement techniques via practical sessions; evaluate viability and limitations of a method during the test design, by correlating to measurement principles and theories; collect and analyse measurement data from different techniques and quantify their respective uncertainties; interpret the experimental results with technical details and insights.\n\nThe syllabus of the unit will include: (1) principles of measurement techniques; (2) experimental test design, plan and set-up; (3) measurement calibration and uncertainty analyses; (4) data post-processing and statistical analyses tools; (5) technical discussion and report preparation.\n\nHow will students, personally, be different as a result of the unit\nWind tunnel tests have been a cornerstone in the aerodynamic development of transport vehicles, renewable wind energy, urban environment, etc., and are increasingly relevant as UK strives to a net-zero carbon by 2050. With this unit, students will gain valuable knowledge and hands-on experience in dedicated wind tunnel facilities with advanced measurement techniques, enhancing their employability for industries that are seeking to recruit experimental experts in aerodynamic testing and data analysis, as well as effective communicators of technical knowledge.\n\nLearning Outcomes\nAfter successful completion of the unit, students will be able to:\n\ndiscuss, evaluate and select state-of-the-art measurement techniques for aerodynamics and aeroacoustics;\ndesign and execute experimental methods using dedicated aerodynamics and aeroacoustics facilities;\nanalyse collected experimental results, including data post-processing, interpretation and uncertainty analysis;\ncommunicate effectively in technical laboratory reports to present experimental data and analysis." . . "Presential"@en . "FALSE" . . "Advanced structural dynamics and aeroelasticity"@en . . "10.00" . "An overview of content\nIn one part of the unit, students will develop an understanding of aeroelastic behaviour of fixed wing aerospace structures, covering static and dynamic aspects of attached and separated flows. In the second part of the unit, students will develop an understanding of aerospace structures with rotors with particular focus on the dynamic properties of rigid and elastic rotors and their aeroelastic interaction with flexible support structures. \n\nHow will students, personally, be different as a result of the unit\nAfter successfully completing this unit, students will be able to appreciate and practically approach complex structural dynamics and aeroelasticity tasks arising during the design, development, and analysis of modern aircraft.\n\nLearning Outcomes\nOn successful completion of the unit the student will be able to: \n\ndiscuss and perform static aeroelastic calculations;\ndiscuss and analyse dynamic aeroelastic stability;\ndevelop and evaluate the response of an aeroelastic systems to atmospheric gusts;\ndevelop mathematical models of aerospace structures with rotors and propellers;\nanalyse dynamic properties of rotating flexible blades and elastically suspended rigid propellers;\nevaluate aeroelastic response and stability characteristics of coupled propeller-wing systems." . . "Presential"@en . "FALSE" . . "Aircraft aerodynamics"@en . . "4.00" . "Course Contents After a short recap on inviscid flow the first part of the course deals with boundary layer theory. Topics addressed are: the\nlaminar boundary layer, the transition process, the turbulent boundary layer, laminar and turbulent flow separation, the\nseparation bubble, lift and drag. The second part of the course starts with general information on drag, useful for the\naerodynamic design of aircraft. The course continues with the analysis and design of single and multi-component airfoils,\nillustrated by examples of CFD analyses and windtunnel experiments. Special topics like winglets, high lift systems, flow control\nand propeller propulsion for sustainable aircraft applications will be treated as well. Some aerodynamic analysis and design\ncodes will be demonstrated during the course.\nStudy Goals The course is designed to provide the student with the basic theoretical and experimental tools for the aerodynamic design of\naircraft. At the end the student will be able to apply basic aerodynamics concepts as well as some usefull design codes." . . "Presential"@en . "TRUE" . . "Rotor / wake aerodynamics"@en . . "4.00" . "Course Contents Introduction to rotary wing aerodynamics. Applications in aircraft, propulsion, fans and wind turbines.\n Conservation laws. Actuator disk/momentum theory. Limitations. Helicopter rotor vertical flight and windmill\nbrake state. Figure of merit. Wind turbine Betz optimum. Lift and drag devices\n Blade elementmomentum method, Tip correction methods. Correction for finite nr. of blades and heavily\nloaded rotors.\n Aerodynamic characteristics of airfoils for rotor application. Aerodynamic properties of pitch and stall\ncontrolled wind turbine. Wind turbine rotor blade design.\n Vortex line methods. Vortex wake structure. Frozen and free wake, vortex core modelling.\n Vortex panel methods. Advanced wake models. Acceleration potential method.\n Detailed rotor near wake structure. Experimental wake velocities and wake vorticity structure.\n 3D effects, Stall delay. Yawed flow and dynamic inflow. Autogiro, helicopter rotor in forward flight.\n Unsteady aerodynamics and dynamic stall effects. Theodorsens Theory. Effects of tower shadow and wind shear.\n Aeroacoustics and rotor aeroacoustics.\n Vertical axis wind turbine rotor and Voight-Schneider propeller\n Effects of inflow turbulence intensity on blade loads. Near and far wake structure\n Wind farm aerodynamics. Rotor-wake interaction. Single and multiple wakes. Effects upon loads and performance.\nStudy Goals Provide an overview of the phenomena and models present in\naerodynamics of rotors, with special emphasis in horizontal axis\nwind turbine rotors. Propellers, vertical axis (crossflow) wind turbine rotors and helicopter rotors\nwill also be addressed, but with less detail.\n\"Hands on\" introduction to the different computational models used nowadays to analyse the\naerodynamics of rotors." . . "Presential"@en . "TRUE" . . "Hypersonic aerodynamics"@en . . "3.00" . "no data" . . "Presential"@en . "FALSE" . . "Fundamentals of aeroelasticity"@en . . "3.00" . "Course Contents This course provides an introduction to the physical and analytical aspects of aeroelasticity.\nThe breakdown of the course is:\n1. Introduction to aeroelasticity and aeroelastic phenomena\n2. Illustration of aeroelastic phenomena using simplified aerodynamic and structural models\n3. Aerodynamic models for aeroelastic analysis\n4. Structural models for aeroelastic analysis\n5. Aeroelastic response to gust excitation\n6. Aeroelastic models in state-space format\n7. Aeroelastic aspects in the design of aircraft\n8. Numerical aeroelastic calculations using custom-programmed software.\nStudy Goals At the end of the course the student should:\n1. understand the physical processes which drive aeroelastic phenomena.\n2. be able to formulate and solve aeroelastic response and instability problems.\n3. be able to identify strengths and weaknesses of different aerodynamic and structural models for the analysis of a given\naeroelastic condition.\n4. be familiar with the role of aeroelasticity in aircraft design.\n5. be able to program and solve simplified aeroelastic problems" . . "Presential"@en . "TRUE" . . "Applied aircraft aeroelasticity"@en . . "3.00" . "no data" . . "Presential"@en . "FALSE" . . "Aircraft structures, loads and aeroelasticity"@en . . "no data" . "This module aims to familiarise students with the fundamentals of aircraft structures and aeroelasticity. It is designed to provide the knowledge to carry out calculation and analysis of aircraft structures, and skills in conceptual aircraft structural design." . . "Presential"@en . "TRUE" . . "Advanced aerodynamics and propulsion systems"@en . . "no data" . "This module provides a more advanced understanding of aircraft aerodynamics and introduces advanced theories and tools for analysis of aircraft aerodynamics." . . "Presential"@en . "TRUE" . . "Fluid structure interaction and aeroelasticity"@en . . "no data" . "This module aims to familiarise students with theories and numerical analysis of linear and nonlinear elastic solids and unsteady aerodynamics. It will help students to numerical techniques for coupling the dynamics of fluid flow and structures." . . "Presential"@en . "FALSE" . . "Aerodynamic design and control of aircrafts"@en . . "5.00" . "no data" . . "Presential"@en . "FALSE" . . "Computational aerodynamics"@en . . "6.0" . "This module aims to develop a basic understanding of the aerodynamic behaviour for both 2D and 3D wings. Students will be required to demonstrate knowledge from Fluid Mechanics leading up to Kutta-Joukowski Theorem. Students then apply General Thin Airfoil theory to develop 2D wing flow characteristics and Prandtl’s lifting line theory to derive Aerodynamic coefficients for 3D finite wings. Students will also be required to apply knowledge through computational methods to demonstrate the derived theory and analyse the aerodynamics of a UAV wing." . . "Presential"@en . "TRUE" . . "Dynamics of aerospace structures"@en . . "6.0" . "This course offers the opportunity to integrate the preparation acquired in the basic courses with advanced methodologies and tools for the dynamic analysis of aerospace structures in time and Fourier-Laplace domain. The response of linear structural systems to both deterministic and stochastic dynamic loads is studied, introducing some essential issues on random vibration theory. The course also presents order reduction techniques (static and dynamic condensation) of finite element models together with seismic excitation problems on aerospace structures such as aircraft and launchers. A special focus is also given to the main structural damping models for studying vibration control with dynamic absorbers. Finally, an overview is given of propagation problems in aerospace structures in which fast dynamic processes are involved. Numerical integration methods are used to study the responses of these structural systems, highlighting the differences with respect to the responses obtained with linear analysis.\n\nLearning objectives\nGeneral\nAfter completing this course, the student will be able to understand all the fundamental aspects related to the dynamics of aerospace structures, study the problems of response to random seismic loads with performance evaluation, design a passive and active control system of structural vibrations using dynamic absorbers and evaluate nonlinear effects in the case of structures characterized by fast dynamics. Finally, the student will have matured the cultural background to dialogue with certification bodies for the qualification to fly / launch of structural systems and with the bodies / professionals responsible for experimental dynamic tests." . . "Presential"@en . "TRUE" .