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NASA-TM-X-3160

Experimental and theoretical low speed aerodynamic characteristics of the NACA 65 sub 1-213, alpha equals 0.50, airfoil

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:28:34Z
date available2017-09-04T15:28:34Z
date copyright01/01/1975
date issued1975
identifier otherNUTKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/29650
description abstractLow-speed wind-tunnel tests have been conducted to determine the two-dimensional aerodynamic characteristics of the NACA 65 sub 1-213, a = 0.05, airfoil. The results were compared with data from another low-speed wind tunnel and also with theoretical predictions obtained by using a viscous subsonic method. The tests were conducted over a Mach number range from 0.10 to 0.36. Reynolds numbers based on the airfoil chord varied from about 3 million to 23 million.
languageEnglish
titleNASA-TM-X-3160num
titleExperimental and theoretical low speed aerodynamic characteristics of the NACA 65 sub 1-213, alpha equals 0.50, airfoilen
typestandard
page76
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1975
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRFOIL
subject keywordsCHARACTERISTICS
subject keywordsCOEFFICIENTS
subject keywordsDATA
subject keywordsDIMENSIONAL
subject keywordsFLOW
subject keywordsGEOMETRY
subject keywordsLOW
subject keywordsPROCESSING
subject keywordsPROFILES
subject keywordsSPEED
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsTWO
subject keywordsVISCOUS
subject keywordsWIND


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