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NACA-TN-3162
Effects of subsonic Mach number on the forces and pressure distributions on four NACA 64A-series airfoil sections at angles of attack as high as 28 degrees
Year: 1954
Abstract: Lift, drag, moment, and pressure-distribution measurements have been made for the NACA 64A010, 64A410, 64A006, and 64A406 airfoil sections at high subsonic Mach numbers. The tests were made for angles of attack as high as 280 and for Mach numbers ranging from 0.30 to about 0.93 with corresponding Reynolds numbers varying from approximately 0.9 X 106 to 1.9 X 106.
A comparison of the maximum lift coefficients from NACA TN 2096 for 10-percent-chord-thick NACA 64A-series airfoil sections cambered with a = 1.0 and a = 0.4 mean lines with those of the present report for the NACA 64A410 airfoil section cambered with the a = 0.8 (modified) mean line indicated that the a = 0.8 (modified) mean line was superior for providing high maximum lift coefficients throughout the Mach number range, especially for Mach numbers above about 0.6.
A comparison of the maximum lift coefficients from NACA TN 2096 for 10-percent-chord-thick NACA 64A-series airfoil sections cambered with a = 1.0 and a = 0.4 mean lines with those of the present report for the NACA 64A410 airfoil section cambered with the a = 0.8 (modified) mean line indicated that the a = 0.8 (modified) mean line was superior for providing high maximum lift coefficients throughout the Mach number range, especially for Mach numbers above about 0.6.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:39:49Z | |
| date available | 2017-09-04T17:39:49Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | DTNUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsein=autho9279AF67081DAC4/handle/yse/162760 | |
| description abstract | Lift, drag, moment, and pressure-distribution measurements have been made for the NACA 64A010, 64A410, 64A006, and 64A406 airfoil sections at high subsonic Mach numbers. The tests were made for angles of attack as high as 280 and for Mach numbers ranging from 0.30 to about 0.93 with corresponding Reynolds numbers varying from approximately 0.9 X 106 to 1.9 X 106. A comparison of the maximum lift coefficients from NACA TN 2096 for 10-percent-chord-thick NACA 64A-series airfoil sections cambered with a = 1.0 and a = 0.4 mean lines with those of the present report for the NACA 64A410 airfoil section cambered with the a = 0.8 (modified) mean line indicated that the a = 0.8 (modified) mean line was superior for providing high maximum lift coefficients throughout the Mach number range, especially for Mach numbers above about 0.6. | |
| language | English | |
| title | NACA-TN-3162 | num |
| title | Effects of subsonic Mach number on the forces and pressure distributions on four NACA 64A-series airfoil sections at angles of attack as high as 28 degrees | en |
| type | standard | |
| page | 146 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |