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Nozzle wall roughness effects on free-stream noise and transition in the pilot low-disturbance tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Beckwith, I. E. Creel Jr., T. R. Chen, F. J. |
| Copyright Year | 1985 |
| Description | An investigation at Mach 3.5 into the effects of nozzle wall roughness on free stream pressure fluctuations and cone transition Reynolds numbers was conducted in the pilot low disturbance tunnel at the Langley Research Center. Nozzle wall roughness caused by either particle deposits or imperfections in surface finish increased free stream noise levels and reduced the transition Reynolds numbers on a cone mounted in the test rhombus. |
| File Size | 4335163 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850026042 |
| Archival Resource Key | ark:/13960/t4xh4gp6m |
| Language | English |
| Publisher Date | 1985-09-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Conical Nozzles Nozzle Flow Reynolds Number Supersonic Wind Tunnels Wind Tunnel Tests Aerodynamic Noise Boundary Layer Transition Transition Flow Free Flow Aerodynamic Characteristics Mach Number 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 |