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NACA-ACR-L5F13 REV A
Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil
Year: 1945
Abstract: An 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.
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.
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NACA-ACR-L5F13 REV A
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:22:02Z | |
| date available | 2017-09-04T17:22:02Z | |
| date copyright | 01/01/1945 | |
| date issued | 1945 | |
| identifier other | ZUUYYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/145233 | |
| description abstract | An 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. | |
| language | English | |
| title | NACA-ACR-L5F13 REV A | num |
| title | Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil | en |
| type | standard | |
| page | 44 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1945 | |
| contenttype | fulltext |