Loading...
Please wait, while we are loading the content...
Similar Documents
Two-dimensional wind-tunnel investigation of modified naca 65(112)-111 airfoil with 35-percent-chord slotted flap to determine optimum flap configuration at reynolds number of 2.4 million
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1947 |
| Description | An investigation has been made in the Langley two-dimensional low-turbulence tunnel to develop the optimum configuration of a 0.35-chord slotted flap on an NACA 65 (112)-111 airfoil section modified by removing the trailing-edge cusp. The results of the investigation indicate that for the optimum configuration at a Reynolds number of 2.4 x 10(exp 6), the flap deflection was 45 degrees and the flap leading-edge radius center was 0.73 percent-chord behind and 4.46 percent-chord below the slot lip. The maximum section lift coefficient for the optimum configuration at a Reynolds number of 2.4 x 10(exp 6) was 2.46 or 0.12 higher than that obtained for an NACA 65-210 airfoil section with a 0.250-chord slotted flap. |
| File Size | 358392 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050019580 |
| Archival Resource Key | ark:/13960/t47q3b031 |
| Language | English |
| Publisher Date | 1947-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
