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The effectiveness at high speeds of a 10-percent-chord plain trailing-edge flap on the naca 65-210 airfoil section
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1948 |
| Description | This report contains the results of a high-speed wind-tunnel investigation of the effectiveness of a 10-percent-chord plain flap on the NACA 65-210 airfoil section. The results include an indication of the lift-producing characteristics and the effectiveness of the 10-percent-chord flap. From a comparison of the characteristics of the 10-percent-chord flap with those of a 20-percent-chord flap it was concluded that, although a reduction in flap-chord ratio from 0.20 to 0.10 lessens the severity of the effectiveness loss at supercritical speeds, the 20-percent-chord flap is more effective throughout the entire range of Mach numbers from 0.3 to 0.875. |
| File Size | 898781 |
| Page Count | 28 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930085383 |
| Archival Resource Key | ark:/13960/t6rz3m339 |
| Language | English |
| Publisher Date | 1948-06-14 |
| Access Restriction | Open |
| Subject Keyword | Controls, Flap Type - Wing Sections Flaps, Plain - Wing Section Mach Number Effects Wing Sections 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 |
