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Flat-plate drag measurements with vortex generators in turbulent boundary layer
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Mehrotra, S. C. Rao, D. M. |
| Copyright Year | 1983 |
| Description | Direct drag measurements were obtained on a flat plate with a spanwise row of vortex generators near the leading edge, to produce an array of stream wise vortices within the approaching turbulent boundary layer. The object was to explore the possibility of modifying the large scale structure of the boundary layer through embedded longitudinal vortices with a view to obtaining a reduction in wall shear. Both obstacle and vane type vortex generators were tested at free stream velocities 40 ft/sec to 130 ft/sec corresponding to plate length Reynolds no. 0.3 million to 0.8 million with a nominal boundary layer thickness of approximately 0.6 in. at the leading edge. A few vortex generator configurations were tested both on and off the plate to measure the total drag as well as the plate drag alone. The obstacle type devices reduced the plate drag, indicating that the wake momentum defect predominated even in the presence of streamwise vortices. The vane type vortex generators however always increased the plate drag. |
| File Size | 387829 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830018543 |
| Archival Resource Key | ark:/13960/t4gn31n96 |
| Language | English |
| Publisher Date | 1983-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Flat Plates Drag Reduction Vortices Reynolds Number Wall Flow Turbulent Boundary Layer Vortex Generators Drag Measurement Leading Edges Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
