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NACA-TR-668

Wind-tunnel investigation of N.A.C.A. 23012, 23021, and 23030 airfoils with various sizes of split flap

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:00:08Z
date available2017-09-04T18:00:08Z
date copyright01/01/1939
date issued1939
identifier otherFVWUYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/183179
description abstractReport presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-chord NACA and 23021, and 23030 airfoils with split flaps 10, 20, 30, and 40 percent of the wing chord to determine the section aerodynamic characteristics of the airfoils as affected by airfoil thickness, flap chord, and flap deflection. The complete section aerodynamic characteristics of all the combinations tested are given in the form of graphs of lift, drag, and pitching-moment coefficients, and certain applications to aerodynamic design are discussed.
languageEnglish
titleNACA-TR-668num
titleWind-tunnel investigation of N.A.C.A. 23012, 23021, and 23030 airfoils with various sizes of split flapen
typestandard
page18
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1939
contenttypefulltext
subject keywordsAERODYNAMIC
subject keywordsAIRFOIL
subject keywordsAIRFOILS
subject keywordsCHARACTERISTICS
subject keywordsCOEFFICIENTS
subject keywordsDEFLECTION
subject keywordsDRAG
subject keywordsFLAPS
subject keywordsLIFT
subject keywordsMOMENTS
subject keywordsNUMBER
subject keywordsPITCHING
subject keywordsPROFILES
subject keywordsREYNOLDS
subject keywordsSPLIT
subject keywordsTESTS
subject keywordsTHICKNESS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING


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