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| 01600nam 2200301za 4500 |
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| 001 | 9.821353 |
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| 003 | CaOODSP |
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| 005 | 20240219183447 |
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| 007 | cr ||||||||||| |
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| 008 | 160720s2013 onc|||||o f000 0 eng d |
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| 040 | |aCaOODSP|beng |
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| 041 | |aeng|bfre |
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| 043 | |an-cn--- |
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| 086 | 1 |aD68-6/178-2013E-PDF |
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| 100 | 1 |aHally, David. |
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| 245 | 10|aSmoothing propeller tip geometry for use in a RANS solver |h[electronic resource] / |cby David Hally. |
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| 260 | |a[Ottawa] : |bDefence Research and Development Canada, |cc2013. |
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| 300 | |avi, 26 p. : |btables, graphs. |
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| 490 | 1 |aTechnical Memorandum ; |v2013-178 |
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| 500 | |a"October 2013." |
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| 504 | |aIncludes bibliographical references. |
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| 520 | |aThe traditional method of specifying propeller geometry is to define a series of airfoil sections each of which is modified by local values of the chord length, pitch, skew angle and rake. Near the tip of the propeller, where the chord length reduces rapidly to zero, a blade defined in this way often has surface irregularities which make meshing for flow solvers difficult. Methods are described for smoothing the irregularities and saving the resulting propeller geometry in the IGES format which can be read by most flow solvers. |
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| 692 | 07|2gccst|aTechnical reports |
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| 693 | 07|aPropellers |
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| 693 | 07|aComputational fluid dynamics |
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| 710 | 2 |aDefence R&D Canada. |
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| 830 | #0|aTechnical memorandum (Defence R&D Canada)|v2013-178|w(CaOODSP)9.820564 |
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| 856 | 40|qPDF|s1.01 MB|uhttps://publications.gc.ca/collections/collection_2016/rddc-drdc/D68-6-178-2013-eng.pdf |
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