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Influence of airfoil trailing-edge angle and trailing-edge-thickness variation on the effectiveness of a plain flap at high subsonic Mach numbers
| Content Provider | University of North Texas |
|---|---|
| Author | Hemenover, Albert D. Graham, Donald J. |
| Organization | Ames Aeronautical Laboratory (U.S.) |
| Description | Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap as determined from wind tunnel tests over a range of Mach numbers. Results regarding the section lift and pitching-moment characteristics, variation of lift coefficient with flap deflection, schileren photographs, and effect of angle of attack are provided. |
| File Format | |
| Archival Resource Key | ark:/67531/metadc58719 |
| Language | English |
| Publisher Date | 2018-05-29 |
| Access Restriction | Open |
| Subject Keyword | lift characteristics aircraft flaps |
| Content Type | Text |
| Resource Type | Report |