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Flow-field measurements on an airfoil with an oscillating trailing-edge using holographic interferometry
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Bachalo, W. D. |
| Copyright Year | 1984 |
| Description | Holographic interferometry data were acquired on an NACA 64A010 airfoil with an oscillating flap. The airfoil was installed in the Ames 11-Foot Transonic Wind Tunnel between splitter plates. Recordings were made at discrete phase angles of the oscillation. The interferometry results provided detailed flow visualization of the shock boundary-layer interaction and the separated flow. Quantitative results were extracted from the interferograms to produce pressure data. These results were compared to the surface pressures obtained with the surface pressure taps. Excellent agreement was found for low angles of incidence. At larger angles of incidence, the flow had greater three-dimensionality, and the results were not in good agreement in some regions of the flow field. Mach contours were traced for representative flow conditions. Wake profiles were also obtained using the assumption of constant pressure across the wake and the Crocco relationship. |
| File Size | 9420612 |
| Page Count | 149 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840026359 |
| Archival Resource Key | ark:/13960/t3rv5d473 |
| Language | English |
| Publisher Date | 1984-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Transonic Flow Transonic Wind Tunnels Flow Distribution Flaps Control Surfaces Flow Visualization Oscillations Angles Geometry Holographic Interferometry Unsteady Flow Separated Flow Incidence Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
