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The cryogenic wind tunnel concept for high reynolds number testing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Adcock, J. B. Davenport, E. E. Goodyer, M. J. Kilgore, R. A. |
| Copyright Year | 1974 |
| Description | Theoretical considerations indicate that cooling the wind-tunnel test gas to cryogenic temperatures will provide a large increase in Reynolds number with no increase in dynamic pressure while reducing the tunnel drive-power requirements. Studies were made to determine the expected variations of Reynolds number and other parameters over wide ranges of Mach number, pressure, and temperature, with due regard to avoiding liquefaction. Practical operational procedures were developed in a low-speed cryogenic tunnel. Aerodynamic experiments in the facility demonstrated the theoretically predicted variations in Reynolds number and drive power. The continuous-flow-fan-driven tunnel is shown to be particularly well suited to take full advantage of operating at cryogenic temperatures. |
| File Size | 5203982 |
| Page Count | 96 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19750003928 |
| Archival Resource Key | ark:/13960/t2j72723q |
| Language | English |
| Publisher Date | 1974-11-01 |
| Access Restriction | Open |
| Subject Keyword | Research And Support Facilities (air) Liquefaction Gas Flow Reynolds Number Cryogenics Wind Tunnel Tests Wind Tunnel Drives Wind Tunnel Models Aeroelasticity Mach Number Dynamic Pressure 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 |
