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The boundary layer on compressor cascade blades (Document No: 19810014883)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Deutsch, S. |
| Copyright Year | 1981 |
| Description | The flow field about an airfoil in cascade at a Reynolds number of 5 x 10 to the 5th power is described. Hot wire and laser anemometry are combined with flow visualization techniques in order to obtain detailed flow data (e.g., boundary layer profiles, points of separation, and the transition zone) on a cascade of relatively highly loaded blades. Benchmark data is provided for the evaluation of current and future predictive models, in this way aiding in the compressor design process. |
| File Size | 399721 |
| Page Count | 9 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810014883 |
| Archival Resource Key | ark:/13960/t0gv0dt2f |
| Language | English |
| Publisher Date | 1981-06-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Cascade Flow Turbulent Flow Compressor Blades Fluid Dynamics Hot-wire Anemometers Flow Visualization Velocity Distribution Boundary Layers 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 |
