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Experimental results for a flapped natural-laminar-flow airfoil with high lift/drag ratio
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | McGhee, R. J. Beasley, W. D. Viken, J. K. Harvey, W. D. Pfenninger, W. |
| Copyright Year | 1984 |
| Description | Experimental results have been obtained for a flapped natural-laminar-flow airfoil, NLF(1)-0414F, in the Langley Low-Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.05 to 0.40 and a chord Reynolds number range from about 3.0 x 10(6) to 22.0 x 10(6). The airfoil was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40, a Reynolds number of 10.0 x 10(6), and a Mach number of 0.40. A 0.125 chord simple flap was incorporated in the design to increase the low-drag, lift-coefficient range. Results were also obtained for a 0.20 chord split-flap deflected 60 deg. |
| File Size | 13688765 |
| Page Count | 326 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860016814 |
| Archival Resource Key | ark:/13960/t0ms8k02b |
| Language | English |
| Publisher Date | 1984-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aerodynamic Drag Subsonic Speed Lift Drag Ratio Reynolds Number Aerodynamic Coefficients Surface Roughness Lift Laminar Flow Airfoils Wind Tunnel Tests Flaps Control Surfaces Angle of Attack Aerodynamic Characteristics Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
