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NACA-TN-4363
Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5
Year: 1958
Abstract: A simplified method has been devised for determination of the critical height of three-dimensional roughness particles required to promote premature transition of a laminar boundary layer on models of airplanes or airplane components in a wind tunnel with zero heat transfer. A single equation is derived which relates the roughness height to a Reynolds number based on the roughness height and on local flow conditions at the height of the roughness, and charts are presented from which the critical roughness height can be easily obtained for Mach numbers from 0 to 5. A discussion of the use of these charts is presented with consideration of various model configurations.
Subject: AIRCRAFT MODELS
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:45:01Z | |
| date available | 2017-09-04T16:45:01Z | |
| date copyright | 01/01/1958 | |
| date issued | 1958 | |
| identifier other | VYONEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/108355 | |
| description abstract | A simplified method has been devised for determination of the critical height of three-dimensional roughness particles required to promote premature transition of a laminar boundary layer on models of airplanes or airplane components in a wind tunnel with zero heat transfer. A single equation is derived which relates the roughness height to a Reynolds number based on the roughness height and on local flow conditions at the height of the roughness, and charts are presented from which the critical roughness height can be easily obtained for Mach numbers from 0 to 5. A discussion of the use of these charts is presented with consideration of various model configurations. | |
| language | English | |
| title | NACA-TN-4363 | num |
| title | Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5 | en |
| type | standard | |
| page | 20 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1958 | |
| contenttype | fulltext | |
| subject keywords | AIRCRAFT MODELS | |
| subject keywords | BOUNDARY LAYER TRANSITION | |
| subject keywords | FLOW VISUALIZATION | |
| subject keywords | HEIGHT | |
| subject keywords | LAMINAR BOUNDARY LAYER | |
| subject keywords | PARTICLES | |
| subject keywords | SURFACE ROUGHNESS EFFECTS | |
| subject keywords | TURBULENT BOUNDARY LAYER | |
| subject keywords | WIND TUNNEL MODELS |