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Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:22:02Z
date available2017-09-04T17:22:02Z
date copyright01/01/1945
date issued1945
identifier otherZUUYYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=authoCA5893FD081D20686159DD6EFDEC014A/handle/yse/145233
description abstractAn investigation has been made in two-dimensional flow to determine the effect of leakage pas the aileron nose on the aerodynamic characteristics of ailerons. Plain and internally balanced ailerons of 0.20 airfoil chord were tested on an NACA 66(215)-216, A – 1.0 AIRFOIL. The effects of amount and type of leakage, aileron contour, and Mach number and Reynolds number were investigated.
The results of the tests indicated that a small amount of leakage area changed the pressure distributions over the plain and internally balanced ailerons markedly. This change generally resulted in negative increments in the lift and hinge-moment parameters clδ, cha, and chδ. A further increase in the leakage area produced smaller changes in tehse parameters for the internally balanced aileron.
languageEnglish
titleNACA-ACR-L5F13 REV Anum
titleEffect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoilen
typestandard
page44
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1945
contenttypefulltext


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