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Parametric investigation of a high-lift airfoil at high reynolds numbers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Dominik, Chet J. Lin, John C. |
| Copyright Year | 1997 |
| Description | A new two-dimensional, three-element, advanced high-lift research airfoil has been tested in the NASA Langley Research Center s Low-Turbulence Pressure Tunnel at a chord Reynolds number up to 1.6 x 107. The components of this high-lift airfoil have been designed using a incompressible computational code (INS2D). The design was to provide high maximum-lift values while maintaining attached flow on the single-segment flap at landing conditions. The performance of the new NASA research airfoil is compared to a similar reference high-lift airfoil. On the new high-lift airfoil the effects of Reynolds number on slat and flap rigging have been studied experimentally, as well as the Mach number effects. The performance trend of the high-lift design is comparable to that predicted by INS2D over much of the angle-of-attack range. However, the code did not accurately predict the airfoil performance or the configuration-based trends near maximum lift where the compressibility effect could play a major role. |
| File Size | 334485 |
| Page Count | 37 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040110232 |
| Archival Resource Key | ark:/13960/t0vq7w133 |
| Language | English |
| Publisher Date | 1997-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance High Reynolds Number Compressibility Effects Reynolds Number Airfoils Angle of Attack Low Turbulence Computer Programs Mach Number Flapping 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 |
