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An experimental study of transonic flow about a supercritical airfoil. static pressure and drag data obtained from tests of a supercritical airfoil and an naca 0012 airfoil at transonic speeds, supplement
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Spaid, F. W. Roos, F. W. Stivers Jr., L. S. Dahlin, J. A. |
| Copyright Year | 1983 |
| Description | Surface static-pressure and drag data obtained from tests of two slightly modified versions of the original NASA Whitcomb airfoil and a model of the NACA 0012 airfoil section are presented. Data for the supercritical airfoil were obtained for a free-stream Mach number range of 0.5 to 0.9, and a chord Reynolds number range of 2 x 10 to the 6th power to 4 x 10 to the 6th power. The NACA 0012 airfoil was tested at a constant chord Reynolds number of 2 x 10 to the 6th power and a free-stream Mach number range of 0.6 to 0.8. |
| File Size | 11207582 |
| Page Count | 230 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830025575 |
| Archival Resource Key | ark:/13960/t17m53t9p |
| Language | English |
| Publisher Date | 1983-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Aerodynamic Drag Shock Waves Performance Tests Transonic Flow Reynolds Number Wind Tunnel Tests Pressure Distribution Supercritical Wings Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
