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NACA-TR-718
Pressure distribution over an NACA 23012 airfoil with a slotted and a split flap
Year: 1941
Abstract: A pressure-distribution investigation has been conducted in the NACA 4 by 6-foot vertical wind tunnel to determine the air loads on an NACA 23012 airfoil in combination with a 25.66-percent-chord slotted flap and a 20-percent-chord split flap. Pressures were measured on both the upper and the lower surfaces of the main airfoil and the flaps for several angles of attack and at several flap settings. The data, presented as pressure diagrams and as graphs of the section coefficients for the flap alone and for the airfoil-flap combinations, are applicable to rib and flap design for a combination of a thick airfoil and a slotted or a split flap. The results of previous tests of a NACA 23012 airfoil with a slotted flap are compared with the present results.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:44:20Z | |
| date available | 2017-09-04T16:44:20Z | |
| date copyright | 01/01/1941 | |
| date issued | 1941 | |
| identifier other | VWWUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/107705 | |
| description abstract | A pressure-distribution investigation has been conducted in the NACA 4 by 6-foot vertical wind tunnel to determine the air loads on an NACA 23012 airfoil in combination with a 25.66-percent-chord slotted flap and a 20-percent-chord split flap. Pressures were measured on both the upper and the lower surfaces of the main airfoil and the flaps for several angles of attack and at several flap settings. The data, presented as pressure diagrams and as graphs of the section coefficients for the flap alone and for the airfoil-flap combinations, are applicable to rib and flap design for a combination of a thick airfoil and a slotted or a split flap. The results of previous tests of a NACA 23012 airfoil with a slotted flap are compared with the present results. | |
| language | English | |
| title | NACA-TR-718 | num |
| title | Pressure distribution over an NACA 23012 airfoil with a slotted and a split flap | en |
| type | standard | |
| page | 26 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1941 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRCRAFT | |
| subject keywords | AIRFOIL | |
| subject keywords | AIRFOILS | |
| subject keywords | ANGLE | |
| subject keywords | ATTACK | |
| subject keywords | CENTER | |
| subject keywords | CHORDS | |
| subject keywords | COEFFICIENTS | |
| subject keywords | DESIGN | |
| subject keywords | DISTRIBUTION | |
| subject keywords | FLAPS | |
| subject keywords | FORCE | |
| subject keywords | GEOMETRY | |
| subject keywords | LOADS | |
| subject keywords | MOMENTS | |
| subject keywords | PITCHING | |
| subject keywords | PRESSURE | |
| subject keywords | PROFILES | |
| subject keywords | SLOTS | |
| subject keywords | SPLIT | |
| subject keywords | STRUCTURES | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND | |
| subject keywords | WING |