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02316nam a2200325Ia 4500 |
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b874af76-537e-4d1e-833b-4181944e6648 |
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20230803000000.0 |
| 008 |
101228s1927 dcua t f000 0 eng d |
| 035 |
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|a (OCoLC-I)703442688
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| 035 |
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|a (OCoLC-M)694464427
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|a LHL
|c LHL
|d LHL
|d CSt
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|a Y 3.N 21/5:8/411
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| 088 |
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|a NACA TM 411
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|a Hegge Zijnen, B. G. Van der
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|a Determining the velocity distribution in the boundary layer of an airfoil fitted with a rotary cylinder /
|c by B.G. Van der Hegge Zijnen
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| 260 |
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|a Washington :
|b National Advisory Committee for Aeronautics,
|c 1927
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| 300 |
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|a 15, [6] p. :
|b ill. ;
|c 27 cm
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| 490 |
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|a Technical memorandum / National Advisory Committee for Aeronautics ;
|v no. 411
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| 500 |
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|a Translated from Report A 129 of the Rijks-Studiedienst voor de Luchtvaart, Amsterdam. Vol. 4, p. 47-65, 1927, and reprinted from De Ingenieur. No. 43, October 23, 1926, by the National Advisory Committee for Aeronautics
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| 520 |
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|a In the closer investigation of the results obtained from a wing model with a rotary cylinder mounted in its leading edge (NACA TM's 307 and 354), the velocity distribution in the vicinity of the surface of the model was determined by a hot-wire anemometer. The results confirmed the belief that the rotary cylinder had considerable effect on the air flow, but demonstrated the fact that the direct influence of the cylinder is confined to a very thin layer in immediate proximity to the surface
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| 590 |
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|a Copy 1 bound with no. 410
|c 8939599 (parent record's ckey).
|b 36105024833282 (item id)
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| 596 |
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|a 31
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| 650 |
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0 |
|a Aerofoils
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| 650 |
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|a Air flow
|x Measurement
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| 650 |
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|a Boundary layer
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| 650 |
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|a Cylinders
|x Aerodynamics
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| 710 |
1 |
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|a United States
|b National Advisory Committee for Aeronautics.
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| 830 |
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|a Technical memorandum (United States. National Advisory Committee for Aeronautics) ;
|v no. 411
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| 999 |
1 |
0 |
|i b874af76-537e-4d1e-833b-4181944e6648
|l a8940544
|s US-CST
|m determining_the_velocity_distribution_in_the_boundary_layer_of_an_airf_____1927_______natioa________________________________________hegge_zijnen__b__g_________________y_3_n_21_5_8_411p
|
| 999 |
1 |
1 |
|l a8940544
|s ISIL:US-CST
|t BKS
|a SAL3 SEE-OTHER
|b 8940544-1001
|c NACA TM 411
|d ALPHANUM
|x STKS-MONO
|y 8940544-1001
|p UNLOANABLE
|