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NASA-TP-1919
Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section
Year: 1981
Abstract: Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:03:14Z | |
| date available | 2017-09-04T16:03:14Z | |
| date copyright | 01/01/1981 | |
| date issued | 1981 | |
| identifier other | RPWWAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/66473 | |
| description abstract | Wind-tunnel tests were conducted in the Langley low-turbulence pressure tunnel to evaluate the effects on performance of modifying a 17-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the pitching-moment coefficient by increasing the forward loading and to increase the climb lift-drag ratio by decreasing the aft upper surface pressure gradient. The tests were conducted over a Mach number range from 0.07 to 0.32, a chord Reynolds number range 1.0 x 10 to the 6th power to 12.0 x 10 to the 6th power, and an angle-of-attack range from about -10 deg to 20 deg. | |
| language | English | |
| title | NASA-TP-1919 | num |
| title | Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section | en |
| type | standard | |
| page | 86 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1981 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRCRAFT | |
| subject keywords | AIRFOIL | |
| subject keywords | AVIATION | |
| subject keywords | COEFFICIENTS | |
| subject keywords | DRAG | |
| subject keywords | FLOW | |
| subject keywords | GENERAL | |
| subject keywords | GRADIENTS | |
| subject keywords | LIFT | |
| subject keywords | LOW | |
| subject keywords | NUMBER | |
| subject keywords | PRESSURE | |
| subject keywords | PROFILES | |
| subject keywords | RATIO | |
| subject keywords | REYNOLDS | |
| subject keywords | SENSORS | |
| subject keywords | SPEED | |
| subject keywords | STABILITY | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | TURBULENT | |
| subject keywords | WIND |