درباره ما
NACA-ARR-L4D03
Wind-tunnel investigation of control-surface characteristics XVI - pressure distribution over an NACA 0009 airfoil with 0.30-airfoil-chord beveled-trailing-edge flaps
Year: 1944
Abstract: Pressure-distribution tests have been made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel" chords were 15 and 20 percent of the flap chord. The 15-percent bevel was tested with the bevel corner faired with both large and small radii. The purpose of these tests was to supply pressure distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces.
The results are presented as diagrams of resultant pressure coefficients and of increments of resultant pressure coefficient for the airfoil with the flap having beveled trailing edges. The diagrams are presented for the control surface with the gap at the flap nose sealed and unsealed.
The results are presented as diagrams of resultant pressure coefficients and of increments of resultant pressure coefficient for the airfoil with the flap having beveled trailing edges. The diagrams are presented for the control surface with the gap at the flap nose sealed and unsealed.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:37:43Z | |
| date available | 2017-09-04T15:37:43Z | |
| date copyright | 01/01/1944 | |
| date issued | 1944 | |
| identifier other | OVUYYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/39632 | |
| description abstract | Pressure-distribution tests have been made in the NACA 4- by 6-foot vertical tunnel of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel" chords were 15 and 20 percent of the flap chord. The 15-percent bevel was tested with the bevel corner faired with both large and small radii. The purpose of these tests was to supply pressure distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces. The results are presented as diagrams of resultant pressure coefficients and of increments of resultant pressure coefficient for the airfoil with the flap having beveled trailing edges. The diagrams are presented for the control surface with the gap at the flap nose sealed and unsealed. | |
| language | English | |
| title | NACA-ARR-L4D03 | num |
| title | Wind-tunnel investigation of control-surface characteristics XVI - pressure distribution over an NACA 0009 airfoil with 0.30-airfoil-chord beveled-trailing-edge flaps | en |
| type | standard | |
| page | 71 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1944 | |
| contenttype | fulltext |