Show simple item record

NACA-TN-1417

High-speed wind-tunnel tests of an NACA 0009-64 airfoil having a 33.4-percent-chord flap with an overhang 20.1 percent of the flap chord

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:13:38Z
date available2017-09-04T15:13:38Z
date copyright01/01/1947
date issued1947
identifier otherMATSYDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/12308
description abstractINTRODUCTION
Flight and wind-tunnel studies have show that compressibility will have serious adverse effects on the characteristics of the usual flap type control surface. In order to investigate these effects two flapped airfoils were tested in the Langley 24-inch high-speed tunnel. Tests of the first airfoil, and NACA 16-009, were reported in reference 1. The results of the tests of the second airfoil, an NACA 0009-64, are given herein.
languageEnglish
titleNACA-TN-1417num
titleHigh-speed wind-tunnel tests of an NACA 0009-64 airfoil having a 33.4-percent-chord flap with an overhang 20.1 percent of the flap chorden
typestandard
page34
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1947
contenttypefulltext
subject keywordsAIRFOILS
subject keywordsCHAR
subject keywordsCHARACTERISTICS
subject keywordsCOMPRESSIBILITY
subject keywordsEFFECT
subject keywordsFLAPS
subject keywordsHIGH
subject keywordsMOMENTS
subject keywordsNACA
subject keywordsOVERHANG
subject keywordsSPEED
subject keywordsTESTS
subject keywordsTUNNEL
subject keywordsWIND
subject keywordsWING


Files in this item

Thumbnail
Name:
MATSYDAAAAAAAAAA.pdf
Size:
786.2Kb
Format:
PDF
View/Open

This item appears in the following Collection(s)

Show simple item record