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NACA-TN-2753
Effects of Mach number variation between 0.07 and 0.34 and Reynolds number variation between 0.97 x 10(exp 6) and 8.10 x 10(exp 6) power on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections
Year: 1952
Abstract: The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested through the speed range of the Langley 19-foot pressure tunnel at two values of air pressure. The ranges of Mach number obtained were from 0.07 to 0.34 at atmospheric pressure and from 0.08 to 0.26 at a pressure of 33 pounds per square inch absolute. The corresponding Reynolds number ranges were from 0.97 X 106 to 4.44 X 106 and from 2.20 X 106 to 8.10 X 106, respectively. The tests were made with and without partial-span and full-span split flaps deflected 60°. Pressure-distribution measurements were obtained for all configurations.
Subject: COMPLETE
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:38:27Z | |
| date available | 2017-09-04T16:38:27Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | VILUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/102052 | |
| description abstract | The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested through the speed range of the Langley 19-foot pressure tunnel at two values of air pressure. The ranges of Mach number obtained were from 0.07 to 0.34 at atmospheric pressure and from 0.08 to 0.26 at a pressure of 33 pounds per square inch absolute. The corresponding Reynolds number ranges were from 0.97 X 106 to 4.44 X 106 and from 2.20 X 106 to 8.10 X 106, respectively. The tests were made with and without partial-span and full-span split flaps deflected 60°. Pressure-distribution measurements were obtained for all configurations. | |
| language | English | |
| title | NACA-TN-2753 | num |
| title | Effects of Mach number variation between 0.07 and 0.34 and Reynolds number variation between 0.97 x 10(exp 6) and 8.10 x 10(exp 6) power on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections | en |
| type | standard | |
| page | 35 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext | |
| subject keywords | COMPLETE | |
| subject keywords | CONDITIONS | |
| subject keywords | EDGE | |
| subject keywords | EFFECTS | |
| subject keywords | FLAPS | |
| subject keywords | FLOW | |
| subject keywords | MACH | |
| subject keywords | NUMBER | |
| subject keywords | REYNOLDS | |
| subject keywords | SUBSONIC | |
| subject keywords | SURFACE | |
| subject keywords | TRAILING | |
| subject keywords | VISCOUS | |
| subject keywords | WINGS |