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NASA-TP-1786

Low-speed aerodynamic characteristics of a 17-percent-thick medium-speed airfoil designed for general aviation applications

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:57:52Z
date available2017-09-04T17:57:52Z
date copyright01/01/1980
date issued1980
identifier otherFPWWAEAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/180936
description abstractWind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.
languageEnglish
titleNASA-TP-1786num
titleLow-speed aerodynamic characteristics of a 17-percent-thick medium-speed airfoil designed for general aviation applicationsen
typestandard
page86
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1980
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsAIRFOIL
subject keywordsAIRFOILS
subject keywordsANGLE
subject keywordsATTACK
subject keywordsAVIATION
subject keywordsCHARACTERISTICS
subject keywordsCOEFFICIENTS
subject keywordsGENERAL
subject keywordsLOW
subject keywordsMACH
subject keywordsMOMENTS
subject keywordsNUMBER
subject keywordsPITCHING
subject keywordsPROFILES
subject keywordsRATIO
subject keywordsSPEED
subject keywordsTESTS
subject keywordsTHICKNESS
subject keywordsTUNNEL
subject keywordsWIND


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