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Description and calibration of the langley 6- by 28-inch transonic tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ladson, C. L. |
| Copyright Year | 1975 |
| Description | The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility with slotted top and bottom walls, used for testing two dimensional airfoil sections. Basic tunnel-empty Mach number distributions, noise surveys, and test section total pressure surveys are presented. The Mach number capability of the facility is from about 0.3 to 1.2. The stagnation pressure can be varied from 207 kN/sq m (30 lb/sq in) absolute to 620 kN/sq m (90 lb/sq in) absolute. This range of pressure can provide a Reynolds number of about 10 million, based on a 15.2 cm (6.0 in.) model chord at Mach numbers from 0.5 to 1.0. The maximum Reynolds number capability at a Mach number of 1.0 is about 15 million, based on the same model chord. |
| File Size | 3572911 |
| Page Count | 68 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760004992 |
| Archival Resource Key | ark:/13960/t59d1qj3s |
| Language | English |
| Publisher Date | 1975-12-01 |
| Access Restriction | Open |
| Subject Keyword | Research And Support Facilities (air) Stagnation Pressure Two Dimensional Bodies Reynolds Number Transonic Wind Tunnels Airfoils Wind Tunnel Calibration Mach Number Sound 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 |
