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| 001 |
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20150922145318.0 |
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m fo d |
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cr unu|||||||| |
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121121s2012 txu obm 000 0 eng d |
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|a (OCoLC)ocn818906208
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| 035 |
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|a (OCoLC)818906208
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| 035 |
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|a (TxCM)http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11476
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| 040 |
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|a TXA
|c TXA
|d UtOrBLW
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| 049 |
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|a TXAM
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| 099 |
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|a 2012
|a Thesis
|a 1969.1/ETD-TAMU-2012-08-11476
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|a Freels, Justin Reed.
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|a An examination of configurations for using infrared to measure boundary layer transition /
|c by Justin Reed Freels.
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| 264 |
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|a [College Station, Tex.] :
|b [Texas A&M University],
|c [2012]
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|a 1 online resource.
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| 336 |
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|a text
|b txt
|2 rdacontent
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| 337 |
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|a computer
|b c
|2 rdamedia
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| 338 |
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|a online resource
|b cr
|2 rdacarrier
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| 500 |
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|a "Major Subject: Aerospace Engineering"
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| 588 |
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|a Description from author supplied metadata (automated record created 2012-10-22 13:24:58).
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| 502 |
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|b Master of Science
|c Texas A&M University
|d 2012
|o http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11476
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|a Includes bibliographical references.
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|a Text (Thesis)
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|a Infrared transition location estimates can be fast and useful measurements in wind tunnel and flight tests. Because turbulent boundary layers have a much higher rate of convective heat transfer than laminar boundary layers, a difference in surface temperature can be observed between turbulent and laminar regions of an airfoil at a different temperature than the free stream air temperature. Various implementations of this technique are examined in a wind tunnel. These include using a heat lamp as an external source and circulating fluid inside of the airfoil. Furthermore, ABS plastic and aluminum airfoils are tested with and without coatings such as black paint and surface wraps. The results show that thermal conduction within the model and surface reflections are the driving issues in designing an IR system for detecting transition. Aluminum has a high thermal diffusivity so is a poor choice for this method. However, its performance can be improved using an insulating layer. Internal fluid circulation was far more successful than the heat lamp because it eliminates the reflected IR due to the heat lamp. However, using smooth surface wraps can mitigate reflection issues caused by the heat lamps by reducing the scatter within the reflection, producing an IR image with fewer contaminating reflections.
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|a Electronic resource.
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|a Major Aerospace Engineering.
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|a IR thermography
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| 653 |
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|a wind tunnel testing
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| 653 |
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|a experimental aerodynamics
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| 653 |
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|a infrared thermography
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| 653 |
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|a boundary layer transition
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| 653 |
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|a turbulent boundary layer
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|a laminar-to-turbulent transition
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| 653 |
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|a aerodynamics
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| 700 |
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|a White, Edward B.,
|e thesis advisor.
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| 856 |
4 |
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|u http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11476
|z Link to OAK Trust copy
|t 0
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| 948 |
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|a cataloged
|b h
|c 2012/11/21
|d o
|e jstorlie
|f 4:02:06 pm
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| 994 |
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|a C0
|b TXA
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| 999 |
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|a MARS
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| 999 |
f |
f |
|s 12990920-f8e2-3ab8-bc59-70b16693c934
|i 015f563e-fe16-34be-a978-c42499a8ded2
|t 0
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| 952 |
f |
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|a Texas A&M University
|b College Station
|c Electronic Resources
|d Available Online
|t 0
|e 2012 Thesis 1969.1/ETD-TAMU-2012-08-11476
|h Other scheme
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| 998 |
f |
f |
|a 2012 Thesis 1969.1/ETD-TAMU-2012-08-11476
|t 0
|l Available Online
|