The development of a perturbed, incompressible, turbulent boundary layer
January 1969
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| Format: | Technical Report |
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Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1969]
2016
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| Online Access: | http://hdl.handle.net/1721.1/104686 |
| _version_ | 1826206763275255808 |
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| author | Handa, Hisayuki |
| author2 | Massachusetts Institute of Technology. Gas Turbine Laboratory |
| author_facet | Massachusetts Institute of Technology. Gas Turbine Laboratory Handa, Hisayuki |
| author_sort | Handa, Hisayuki |
| collection | MIT |
| description | January 1969 |
| first_indexed | 2024-09-23T13:38:11Z |
| format | Technical Report |
| id | mit-1721.1/104686 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T13:38:11Z |
| publishDate | 2016 |
| publisher | Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1969] |
| record_format | dspace |
| spelling | mit-1721.1/1046862019-04-10T22:52:03Z The development of a perturbed, incompressible, turbulent boundary layer Handa, Hisayuki Massachusetts Institute of Technology. Gas Turbine Laboratory TJ267.A1 M37 no.96 Boundary layer Turbomachines Fluid dynamics Mach number January 1969 Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 1969 Includes bibliographical references (leaves 27-29, 2nd group) The response of a fully-developed equilibrium turbulent boundary layer to a small disturbance was observed experimentally under low-Mach number conditions: a turbulent boundary layer in an axisymmetric channel under zero pressure gradient was perturbed by a single fence like two dimensional protuberance, and the subsequent development of the velocity profile, the turbulent-shear-stress profile, and the wall shear stress was recorded by a constant-temperature hot-wire anemometer and a Preston tube. The height of the five roughness elements used ranged from 0.011 to 0.100 inches (2-15% of the original boundary layer thickness). The perturbation effects are observable only in the vicinity of their origin and each parameter undergoes an individual recovery process. The wall shear stress exhibits a unique style in its development. A perturbed turbulent-shear-stress profile shows a maximum as in the case of a turbulent boundary layer in an adverse pressure gradient. The analysis of the data has revealed a self-preserving feature of the developing velocity profile in form for small enough disturbances: the wall region of the boundary layer is in a local equilibrium after 30 roughness-heights and the unaffected outer layer retains its original characteristics. Under the Sponsorship of: General Electric Company Allison Division of General Motors Company 2016-10-06T21:21:58Z 2016-10-06T21:21:58Z 1969 Technical Report http://hdl.handle.net/1721.1/104686 09166023 GTL report #96 vi, 30, [37] leaves application/pdf Cambridge, Mass. : Gas Turbine Laboratory , Massachusetts Institute of Technology, [1969] |
| spellingShingle | TJ267.A1 M37 no.96 Boundary layer Turbomachines Fluid dynamics Mach number Handa, Hisayuki The development of a perturbed, incompressible, turbulent boundary layer |
| title | The development of a perturbed, incompressible, turbulent boundary layer |
| title_full | The development of a perturbed, incompressible, turbulent boundary layer |
| title_fullStr | The development of a perturbed, incompressible, turbulent boundary layer |
| title_full_unstemmed | The development of a perturbed, incompressible, turbulent boundary layer |
| title_short | The development of a perturbed, incompressible, turbulent boundary layer |
| title_sort | development of a perturbed incompressible turbulent boundary layer |
| topic | TJ267.A1 M37 no.96 Boundary layer Turbomachines Fluid dynamics Mach number |
| url | http://hdl.handle.net/1721.1/104686 |
| work_keys_str_mv | AT handahisayuki thedevelopmentofaperturbedincompressibleturbulentboundarylayer AT handahisayuki developmentofaperturbedincompressibleturbulentboundarylayer |