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Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers (Document No: 19930083553)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1952 |
| Description | Results are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2 x 10 (sup) 6 to 19 x 10 (sup) 6. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain practical design problems. |
| File Size | 11576354 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930083553 |
| Archival Resource Key | ark:/13960/t51g51s0x |
| Language | English |
| Publisher Date | 1952-09-01 |
| Access Restriction | Open |
| Subject Keyword | Flow, Supersonic Diffusers, Supersonic Flow, Laminar Flow, Turbulent 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 |
