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NASA-TM-81912

Low-speed aerodynamic characteristics of a 14-percent-thick NASA phase 2 supercritical airfoil designed for a lift coefficient of 0.7

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:54:45Z
date available2017-09-04T16:54:45Z
date copyright01/01/1980
date issued1980
identifier otherWZMKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/118213
description abstractThe low speed aerodynamic characteristics of a 14 percent thick supercritical airfoil are documented. The wind tunnel test was conducted in the Low Turbulence Pressure Tunnel. The effects of varying chord Reynolds number from 2,000,000 to 18,000,000 at a Mach number of 0.15 and the effects of varying Mach number from 0.10 to 0.32 at a Reynolds number of 6,000,000 are included.
languageEnglish
titleNASA-TM-81912num
titleLow-speed aerodynamic characteristics of a 14-percent-thick NASA phase 2 supercritical airfoil designed for a lift coefficient of 0.7en
typestandard
page101
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1980
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsANGLE
subject keywordsATTACK
subject keywordsCHARACTERISTICS
subject keywordsCOEFFICIENTS
subject keywordsEDGES
subject keywordsLEADING
subject keywordsLIFT
subject keywordsMACH
subject keywordsNUMBER
subject keywordsREYNOLDS
subject keywordsSUPERCRITICAL
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWINGS


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