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An lda (laser-doppler anemometry) investigation of three-dimensional normal shock wave boundary-layer interactions
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Strazisar, A. J. Keith Jr., T. G. Hingst, W. R. Chriss, R. M. |
| Copyright Year | 1989 |
| Description | Nonintrusive measurements were made of a normal shock wave/boundary layer interaction. Two dimensional measurements were made throughout the interaction region while 3-D measurements were made in the vicinity of the shock wave. The measurements were made in the corner of the test section of a continuous supersonic wind tunnel in which a normal shock wave had been stabilized. Laser Doppler Anemometry, surface pressure measurement and flow visualization techniques were employed for two freestream Mach number test cases: 1.6 and 1.3. The former contained separated flow regions and a system of shock waves. The latter was found to be far less complicated. The results define the flow field structure in detail for each case. |
| File Size | 5709874 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19890011585 |
| Archival Resource Key | ark:/13960/t9s22w52t |
| Language | English |
| Publisher Date | 1989-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Normal Shock Waves Laser Doppler Velocimeters Interactional Aerodynamics Supersonic Wind Tunnels Shock Wave Interaction Laser Anemometers Boundary Layer Separation Flow Distribution Wind Tunnel Tests Flow Visualization Pressure Measurement Free Flow Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
