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The nasa langley laminar-flow-control experiment on a swept supercritical airfoil: basic results for slotted configuration
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stack, John P. Harris, Charles D. Brooks Jr., Cuyler W. Clukey, Patricia G. |
| Copyright Year | 1989 |
| Description | The effects of Mach number and Reynolds number on the experimental surface pressure distributions and transition patterns for a large chord, swept supercritical airfoil incorporating an active Laminar Flow Control suction system with spanwise slots are presented. The experiment was conducted in the Langley 8 foot Transonic Pressure Tunnel. Also included is a discussion of the influence of model/tunnel liner interactions on the airfoil pressure distribution. Mach number was varied from 0.40 to 0.82 at two chord Reynolds numbers, 10 and 20 x 1,000,000, and Reynolds number was varied from 10 to 20 x 1,000,000 at the design Mach number. |
| File Size | 39930014 |
| Page Count | 121 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19890012391 |
| Archival Resource Key | ark:/13960/t0ns5np67 |
| Language | English |
| Publisher Date | 1989-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Suction Transonic Flow Supercritical Airfoils Computational Fluid Dynamics Interactional Aerodynamics Reynolds Number Pressure Distribution Wing Slots Boundary Layer Control Laminar Flow Swept Wings Wind Tunnel Tests 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 |
