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16.100 Aerodynamics (MIT) 16.100 Aerodynamics (MIT)

Description

This course extends fluid mechanic concepts from Unified Engineering to the aerodynamic performance of wings and bodies in sub/supersonic regimes. 16.100 generally has four components: subsonic potential flows, including source/vortex panel methods; viscous flows, including laminar and turbulent boundary layers; aerodynamics of airfoils and wings, including thin airfoil theory, lifting line theory, and panel method/interacting boundary layer methods; and supersonic and hypersonic airfoil theory. Course material varies each year depending upon the focus of the design problem. Technical RequirementsFile decompression software, such as Winzip® or StuffIt®, is required to open the .tar files found on this course site. MATLAB&#1 This course extends fluid mechanic concepts from Unified Engineering to the aerodynamic performance of wings and bodies in sub/supersonic regimes. 16.100 generally has four components: subsonic potential flows, including source/vortex panel methods; viscous flows, including laminar and turbulent boundary layers; aerodynamics of airfoils and wings, including thin airfoil theory, lifting line theory, and panel method/interacting boundary layer methods; and supersonic and hypersonic airfoil theory. Course material varies each year depending upon the focus of the design problem. Technical RequirementsFile decompression software, such as Winzip® or StuffIt®, is required to open the .tar files found on this course site. MATLAB&#1

Subjects

aerodynamics | aerodynamics | airflow | airflow | air | air | body | body | aircraft | aircraft | aerodynamic modes | aerodynamic modes | aero | aero | forces | forces | flow | flow | computational | computational | CFD | CFD | aerodynamic analysis | aerodynamic analysis | lift | lift | drag | drag | potential flows | potential flows | imcompressible | imcompressible | supersonic | supersonic | subsonic | subsonic | panel method | panel method | vortex lattice method | vortex lattice method | boudary layer | boudary layer | transition | transition | turbulence | turbulence | inviscid | inviscid | viscous | viscous | euler | euler | navier-stokes | navier-stokes | wind tunnel | wind tunnel | flow similarity | flow similarity | non-dimensional | non-dimensional | mach number | mach number | reynolds number | reynolds number | integral momentum | integral momentum | airfoil | airfoil | wing | wing | stall | stall | friction drag | friction drag | induced drag | induced drag | wave drag | wave drag | pressure drag | pressure drag | fluid element | fluid element | shear strain | shear strain | normal strain | normal strain | vorticity | vorticity | divergence | divergence | substantial derviative | substantial derviative | laminar | laminar | displacement thickness | displacement thickness | momentum thickness | momentum thickness | skin friction | skin friction | separation | separation | velocity profile | velocity profile | 2-d panel | 2-d panel | 3-d vortex | 3-d vortex | thin airfoil | thin airfoil | lifting line | lifting line | aspect ratio | aspect ratio | twist | twist | camber | camber | wing loading | wing loading | roll moments | roll moments | finite volume approximation | finite volume approximation | shocks | shocks | expansion fans | expansion fans | shock-expansion theory | shock-expansion theory | transonic | transonic | critical mach number | critical mach number | wing sweep | wing sweep | Kutta condition | Kutta condition | team project | team project | blended-wing-body | blended-wing-body | computational fluid dynamics | computational fluid dynamics | Incompressible | Incompressible

License

Content within individual OCW courses is (c) by the individual authors unless otherwise noted. MIT OpenCourseWare materials are licensed by the Massachusetts Institute of Technology under a Creative Commons License (Attribution-NonCommercial-ShareAlike). For further information see http://ocw.mit.edu/terms/index.htm

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16.100 Aerodynamics (MIT) 16.100 Aerodynamics (MIT)

Description

This course extends fluid mechanic concepts from Unified Engineering to the aerodynamic performance of wings and bodies in sub/supersonic regimes. 16.100 generally has four components: subsonic potential flows, including source/vortex panel methods; viscous flows, including laminar and turbulent boundary layers; aerodynamics of airfoils and wings, including thin airfoil theory, lifting line theory, and panel method/interacting boundary layer methods; and supersonic and hypersonic airfoil theory. Course material varies each year depending upon the focus of the design problem. This course extends fluid mechanic concepts from Unified Engineering to the aerodynamic performance of wings and bodies in sub/supersonic regimes. 16.100 generally has four components: subsonic potential flows, including source/vortex panel methods; viscous flows, including laminar and turbulent boundary layers; aerodynamics of airfoils and wings, including thin airfoil theory, lifting line theory, and panel method/interacting boundary layer methods; and supersonic and hypersonic airfoil theory. Course material varies each year depending upon the focus of the design problem.

Subjects

aerodynamics | aerodynamics | airflow | airflow | air | air | body | body | aircraft | aircraft | aerodynamic modes | aerodynamic modes | aero | aero | forces | forces | flow | flow | computational | computational | CFD | CFD | aerodynamic analysis | aerodynamic analysis | lift | lift | drag | drag | potential flows | potential flows | imcompressible | imcompressible | supersonic | supersonic | subsonic | subsonic | panel method | panel method | vortex lattice method | vortex lattice method | boudary layer | boudary layer | transition | transition | turbulence | turbulence | inviscid | inviscid | viscous | viscous | euler | euler | navier-stokes | navier-stokes | wind tunnel | wind tunnel | flow similarity | flow similarity | non-dimensional | non-dimensional | mach number | mach number | reynolds number | reynolds number | integral momentum | integral momentum | airfoil | airfoil | wing | wing | stall | stall | friction drag | friction drag | induced drag | induced drag | wave drag | wave drag | pressure drag | pressure drag | fluid element | fluid element | shear strain | shear strain | normal strain | normal strain | vorticity | vorticity | divergence | divergence | substantial derivative | substantial derivative | laminar | laminar | displacement thickness | displacement thickness | momentum thickness | momentum thickness | skin friction | skin friction | separation | separation | velocity profile | velocity profile | 2-d panel | 2-d panel | 3-d vortex | 3-d vortex | thin airfoil | thin airfoil | lifting line | lifting line | aspect ratio | aspect ratio | twist | twist | camber | camber | wing loading | wing loading | roll moments | roll moments | finite volume approximation | finite volume approximation | shocks | shocks | expansion fans | expansion fans | shock-expansion theory | shock-expansion theory | transonic | transonic | critical mach number | critical mach number | wing sweep | wing sweep | Kutta condition | Kutta condition | team project | team project | blended-wing-body | blended-wing-body | computational fluid dynamics | computational fluid dynamics

License

Content within individual OCW courses is (c) by the individual authors unless otherwise noted. MIT OpenCourseWare materials are licensed by the Massachusetts Institute of Technology under a Creative Commons License (Attribution-NonCommercial-ShareAlike). For further information see http://ocw.mit.edu/terms/index.htm

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Atomic Structure and Microstructure of Materials: Crystallographic Texture

Description

This set consists of animations and user controlled simulations of Eulerian cradle, EBSD, CODF, GOSS texture and texture build up. From TLP: Crystallographic Texture

Subjects

crystal | texture | codf | ebsd | x-ray | diffraction | euler | neutron | pole figure | goss | eulerian cradle | doitpoms | university of cambridge | animation | corematerials | ukoer | Engineering | H000

License

Attribution-Noncommercial-Share Alike 2.0 UK: England & Wales Attribution-Noncommercial-Share Alike 2.0 UK: England & Wales http://creativecommons.org/licenses/by-nc-sa/2.0/uk/ http://creativecommons.org/licenses/by-nc-sa/2.0/uk/

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ÁTICAS PARA LA INFORMÁTICA - II (2009)

Description

1.- Familiariza al alumno con los contenidos de la Teoría de Grafos, su manejo y sus múltiples aplicaciones. A lo largo del curso se resuelven problemas tópicos de esta materia relacionados o con utilidad en la Informática desde un punto de vista algorítmico. Se modelizan muchos problemas de la vida "real" como un grafo, para tras aplicarle alguno de los métodos estudiados encontrar una solución. 2.- Se inicia al alumno en técnicas básicas de recuento que permiten averiguar el número de elementos de un conjunto dado sin cortarlos. Las técnicas combinatorias son muy necesarias en Informática dada la frecuencia con la que parecen los problemas combinatorios, en relación con la complejidad de los algoritmos, a la hora de determinar probabilidades de sucesos discretos, etc. 3.-

Subjects

MATEMATICA APLICADA | Grafos | combinatoria | emparejamientos | grafos eulerianos | grafos hamiltonianos | redes

License

http://creativecommons.org/licenses/by-nc-nd/2.5/es/

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ÁTICAS PARA LA INFORMÁTICA - II (2010)

Description

1.- Familiariza al alumno con los contenidos de la Teoría de Grafos, su manejo y sus múltiples aplicaciones. A lo largo del curso se resuelven problemas tópicos de esta materia relacionados o con utilidad en la Informática desde un punto de vista algorítmico. Se modelizan muchos problemas de la vida "real" como un grafo, para tras aplicarle alguno de los métodos estudiados encontrar una solución. 2.- Se inicia al alumno en técnicas básicas de recuento que permiten averiguar el número de elementos de un conjunto dado sin cortarlos. Las técnicas combinatorias son muy necesarias en Informática dada la frecuencia con la que parecen los problemas combinatorios, en relación con la complejidad de los algoritmos, a la hora de determinar probabilidades de sucesos discretos, etc. 3.-

Subjects

MATEMATICA APLICADA | Grafos | combinatoria | emparejamientos | grafos eulerianos | grafos hamiltonianos | redes

License

http://creativecommons.org/licenses/by-nc-nd/2.5/es/

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TALAT Lecture 2301: Design of Members

Description

This lecture gives background to calculation methods for aluminium members in order to understand the specific behavior of statically loaded aluminium alloy structures. Basic structural mechanic, design philosophy and structural aluminium alloys and product forms is assumed.

Subjects

aluminium | aluminum | european aluminium association | eaa | talat | training in aluminium application technologies | training | metallurgy | technology | lecture | design | product | member | joint | static | safety | serviceability | geometrical imperfections | extruded profiles | welded profiles | residual stresses | mechanical properties | bauschinger effect | heat affected zones | stress-strain relationship | strength | reduced strength | partial coefficients | resistance factors | gross section | net section | local buckling | cross section classes | slender plates | effective cross section | class 4 cross sections | deflections of beams | breathing | bending moment | yielding | slenderness parameter | element classification | effective thickness | welded section | section with holes | lateral torsional buckling | axial force | tensile force | compressive force | euler load | squash load | flexural buckling | reduction factor | buckling length | splices | end connections | welded columns | columns with bolt holes | cut-outs | longitudinal welds | transverse welds | columns with unfilled bolt-holes | built-up members | intermediate stiffeners | edge stiffeners | single-sided rib | multi-stiffened plates | orthotropic plates | shear force | plate girder webs | shear buckling | shear resistance | webs with stiffeners | plate girders with intermediate stiffeners | corrugated webs | closely stiffened webs | concentrated loads | beam webs without stiffeners | beam webs with stiffeners | shear centre | closed sections | open sections | torsion without warping | torsion with warpin | bending and axial tension | bending and axial compression | strength of beam-column segments | rectangular section | strain hardening | plastic theory | i-section | h-section | thin walled cross sections | t-section | biaxial bending | linear stress distribution | shear lag | flange curling | lateral deflection | non-symmetrical flanges | corematerials | ukoer | Engineering | H000

License

Attribution-Noncommercial-Share Alike 2.0 UK: England & Wales Attribution-Noncommercial-Share Alike 2.0 UK: England & Wales http://creativecommons.org/licenses/by-nc-sa/2.0/uk/ http://creativecommons.org/licenses/by-nc-sa/2.0/uk/

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16.100 Aerodynamics (MIT)

Description

This course extends fluid mechanic concepts from Unified Engineering to the aerodynamic performance of wings and bodies in sub/supersonic regimes. 16.100 generally has four components: subsonic potential flows, including source/vortex panel methods; viscous flows, including laminar and turbulent boundary layers; aerodynamics of airfoils and wings, including thin airfoil theory, lifting line theory, and panel method/interacting boundary layer methods; and supersonic and hypersonic airfoil theory. Course material varies each year depending upon the focus of the design problem. Technical RequirementsFile decompression software, such as Winzip® or StuffIt®, is required to open the .tar files found on this course site. MATLAB&#1

Subjects

aerodynamics | airflow | air | body | aircraft | aerodynamic modes | aero | forces | flow | computational | CFD | aerodynamic analysis | lift | drag | potential flows | imcompressible | supersonic | subsonic | panel method | vortex lattice method | boudary layer | transition | turbulence | inviscid | viscous | euler | navier-stokes | wind tunnel | flow similarity | non-dimensional | mach number | reynolds number | integral momentum | airfoil | wing | stall | friction drag | induced drag | wave drag | pressure drag | fluid element | shear strain | normal strain | vorticity | divergence | substantial derviative | laminar | displacement thickness | momentum thickness | skin friction | separation | velocity profile | 2-d panel | 3-d vortex | thin airfoil | lifting line | aspect ratio | twist | camber | wing loading | roll moments | finite volume approximation | shocks | expansion fans | shock-expansion theory | transonic | critical mach number | wing sweep | Kutta condition | team project | blended-wing-body | computational fluid dynamics | Incompressible

License

Content within individual OCW courses is (c) by the individual authors unless otherwise noted. MIT OpenCourseWare materials are licensed by the Massachusetts Institute of Technology under a Creative Commons License (Attribution-NonCommercial-ShareAlike). For further information see https://ocw.mit.edu/terms/index.htm

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16.100 Aerodynamics (MIT)

Description

This course extends fluid mechanic concepts from Unified Engineering to the aerodynamic performance of wings and bodies in sub/supersonic regimes. 16.100 generally has four components: subsonic potential flows, including source/vortex panel methods; viscous flows, including laminar and turbulent boundary layers; aerodynamics of airfoils and wings, including thin airfoil theory, lifting line theory, and panel method/interacting boundary layer methods; and supersonic and hypersonic airfoil theory. Course material varies each year depending upon the focus of the design problem.

Subjects

aerodynamics | airflow | air | body | aircraft | aerodynamic modes | aero | forces | flow | computational | CFD | aerodynamic analysis | lift | drag | potential flows | imcompressible | supersonic | subsonic | panel method | vortex lattice method | boudary layer | transition | turbulence | inviscid | viscous | euler | navier-stokes | wind tunnel | flow similarity | non-dimensional | mach number | reynolds number | integral momentum | airfoil | wing | stall | friction drag | induced drag | wave drag | pressure drag | fluid element | shear strain | normal strain | vorticity | divergence | substantial derivative | laminar | displacement thickness | momentum thickness | skin friction | separation | velocity profile | 2-d panel | 3-d vortex | thin airfoil | lifting line | aspect ratio | twist | camber | wing loading | roll moments | finite volume approximation | shocks | expansion fans | shock-expansion theory | transonic | critical mach number | wing sweep | Kutta condition | team project | blended-wing-body | computational fluid dynamics

License

Content within individual OCW courses is (c) by the individual authors unless otherwise noted. MIT OpenCourseWare materials are licensed by the Massachusetts Institute of Technology under a Creative Commons License (Attribution-NonCommercial-ShareAlike). For further information see https://ocw.mit.edu/terms/index.htm

Site sourced from

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