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Model and boundary aerodynamic data from high blockage two-dimensional airfoil tests in a shallow unstreamlined transonic flexible walled test section. [transonic self-streamlining wind tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wolf, S. W. D. Goodyer, M. J. |
| Copyright Year | 1981 |
| Description | Data for a NACA 0012-64 airfoil at Mach numbers of 0.3, 0.5, and 0.7 with the test section flexible walls set in the "straight" position are presented because they may prove useful in the development of wind tunnel correction techniques. |
| File Size | 1677969 |
| Page Count | 98 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810012558 |
| Archival Resource Key | ark:/13960/t3033p18c |
| Language | English |
| Publisher Date | 1981-04-01 |
| Access Restriction | Open |
| Subject Keyword | Research And Support Facilities (air) Flexible Bodies Tables Data Transonic Wind Tunnels Wind Tunnel Tests Airfoils Wind Tunnel Walls Velocity Distribution Two Dimensional Flow Aerodynamic Characteristics Streamlined Bodies Pressure Gradients Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |