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Investigation of operating pressure ratio of a supersonic wind tunnel utilizing distributed boundary-layer suction in test section
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1950 |
| Description | Effect of distributed boundary-layer suction on operating pressure ratio of a supersonic wind tunnel was investigated. Investigation was made in 3.84- by 10-inch supersonic tunnel operating at Mach number 2.0 and suction was applied in neighborhood of the normal shock to two walls of a constant-area extension of test section. A reduction of 4 percent of operating pressure ratio was attributed to improved flow conditions at subsonic-diffuser inlet. The theoretical normal shock was, in practice, replaced by a multiple-branch shock configuration across which the flow parameters changed in approximate accordance with the Rankine-Hugoniot values. |
| File Size | 17348056 |
| Page Count | 40 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086352 |
| Archival Resource Key | ark:/13960/t5fb9db5x |
| Language | English |
| Publisher Date | 1950-11-01 |
| Access Restriction | Open |
| Subject Keyword | 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 |
