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Summary report on the high-speed characteristics of six model wings having NACA 65sub1-series sections

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:11:30Z
date available2017-09-04T18:11:30Z
date copyright01/01/1947
date issued1947
identifier otherGZWUYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/194481
description abstractA summary of the results of wind-tunnel tests to determine the high-speed aerodynamic characteristics of six model wings having NACA 65sub1-series sections is presented in this report. The 8-percent-thick wings were superior to the 10-percent and 12-percent-thick wings from the standpoint of power economy during level flight for Mach numbers above 0.76. However, airplanes that are to fly at Mach numbers below 0.76 will gain aerodynamically if the percentage thickness of the wing and the aspect ratio are both increased. The lift-curve slopes for the 8-percent-thick wings at 0.85 Mach number were roughly twice their low-speed values.
languageEnglish
titleNACA-TR-877num
titleSummary report on the high-speed characteristics of six model wings having NACA 65sub1-series sectionsen
typestandard
page17
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1947
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRCRAFT
subject keywordsAIRFOIL
subject keywordsANGLE
subject keywordsASPECT
subject keywordsATTACK
subject keywordsBOMBER
subject keywordsCHARACTERISTICS
subject keywordsCOEFFICIENTS
subject keywordsDRAG
subject keywordsFLAPS
subject keywordsFLIGHT
subject keywordsHIGH
subject keywordsHORIZONTAL
subject keywordsLIFT
subject keywordsLOADING
subject keywordsMACH
subject keywordsMANEUVERS
subject keywordsMODELS
subject keywordsMOMENTS
subject keywordsNUMBER
subject keywordsPITCHING
subject keywordsPROFILES
subject keywordsRATIO
subject keywordsSPEED
subject keywordsTHIN
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING
subject keywordsWINGS


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