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High reynolds number tests of the nasa sc(2)-0012 airfoil in the langley 0.3-meter transonic cryogenic tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Mineck, Raymond E. Lawing, Pierce L. |
| Copyright Year | 1987 |
| Description | A wind-tunnel investigation of the NASA SC(2)-0012 airfoil has been conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel. This investigation supplements the two-dimensional airfoil studies of the Advanced Technology Airfoil Test Program. The Mach number was varied from 0.60 to 0.84. The stagnation temperature and pressure were varied to provide a Reynolds number range from 6 to 40 x 10 to the 6th power based on a 6.0-in. (15.24-cm) airfoil chord. No corrections for wind-tunnel wall interference have been made to the data. The aerodynamic results are presented as integrated force and moment coefficients and pressure distributions without any analysis. |
| File Size | 14432325 |
| Page Count | 58 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870014161 |
| Archival Resource Key | ark:/13960/t22c3x05g |
| Language | English |
| Publisher Date | 1987-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics High Reynolds Number Supercritical Airfoils Transonic Wind Tunnels Pressure Distribution Airfoils Two Dimensional Flow Moment Distribution Wall Flow Wind Tunnel Tests Symmetrical Bodies Force Distribution Aerodynamic Characteristics Cryogenic Wind Tunnels Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
