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NASA-TN-D-8242

Aerodynamic characteristics of a vane flow angularity sensor system capable of measuring flightpath accelerations for the Mach number range from 0.40 to 2.54

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:00:35Z
date available2017-09-04T17:00:35Z
date copyright01/01/1976
date issued1976
identifier otherXOYKAEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/124068
description abstractThe aerodynamic characteristics of the angle of attack vane and the angle of sideslip vane are summarized. The test conditions ranged in free stream Mach number from 0.40 to 2.54, in angle of attack from -2 deg to 22 deg, in angle of sideslip from -2 deg to 12 deg, and in Reynolds number from 590,000 per meter to 1.8 million per meter. The results of the wind tunnel investigation are compared with results obtained with similar vane configurations. Comparisons with a NACA vane configuration are also made. In addition, wind tunnel-derived upwash for the test installation is compared with analytical predictions.
languageEnglish
titleNASA-TN-D-8242num
titleAerodynamic characteristics of a vane flow angularity sensor system capable of measuring flightpath accelerations for the Mach number range from 0.40 to 2.54en
typestandard
page46
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1976
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsANGLE
subject keywordsATTACK
subject keywordsCHARACTERISTICS
subject keywordsDIRECTION
subject keywordsFLIGHT
subject keywordsFLOW
subject keywordsINDICATORS
subject keywordsMACH
subject keywordsNUMBER
subject keywordsPATHS
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsVANES
subject keywordsVELOCITY
subject keywordsWIND


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