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Effects of wing leading-edge deflection on low-speed aerodynamic characteristics of a low-aspect-ratio highly swept arrow-wing configuration. [wind tunnel tests
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Weston, R. P. Coe Jr., P. L. |
| Copyright Year | 1979 |
| Description | Static force tests were conducted in the Langley V/STOL tunnel at a Reynolds number (based on the mean aerodynamic chord) of about 2.0 x 10 to the 6th power for an angle-of-attack range from about - 10 deg to 17 deg and angles of sideslip of 0 and + or - 5 deg. Limited flow visualization studies were also conducted in order to provide a qualitative assessment of leading-edge upwash characteristics. |
| File Size | 2968216 |
| Page Count | 73 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790017849 |
| Archival Resource Key | ark:/13960/t9p31pn91 |
| Language | English |
| Publisher Date | 1979-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Low Speed Stability Deflection Supersonic Cruise Aircraft Research Low Aspect Ratio Wings Tables Data Arrow Wings Upwash Wind Tunnel Tests Flow Visualization Wind Tunnel Models Aerodynamic Characteristics Leading Edges Graphs Charts Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
