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NASA-TM-78650
Wind-tunnel results for an improved 21-percent-thick low-speed airfoil section
Year: 1978
Abstract: Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:04:42Z | |
| date available | 2017-09-04T18:04:42Z | |
| date copyright | 01/01/1978 | |
| date issued | 1978 | |
| identifier other | GHNKAEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/187597 | |
| description abstract | Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000. | |
| language | English | |
| title | NASA-TM-78650 | num |
| title | Wind-tunnel results for an improved 21-percent-thick low-speed airfoil section | en |
| type | standard | |
| page | 45 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1978 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRFOILS | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | DESIGN | |
| subject keywords | DISTRIBUTION | |
| subject keywords | LOW | |
| subject keywords | NUMBER | |
| subject keywords | PRESSURE | |
| subject keywords | REYNOLDS | |
| subject keywords | SPEED | |
| subject keywords | STRUCTURAL | |
| subject keywords | TESTS | |
| subject keywords | THICKNESS | |
| subject keywords | TUNNEL | |
| subject keywords | TUNNELS | |
| subject keywords | WIND |