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Subsonic longitudinal and lateral directional static stability characteristics of a variable sweep fighter configuration employing various control surface deflections at angles of attack of 0 deg to 50 deg and large sideslip angles
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Grafton, S. B. Huffman, J. K. Fox Jr., C. H. |
| Copyright Year | 1977 |
| Description | A variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edge slats and trailing edge flaps on the outboard panels was tested at a Mach number of 0.15 in the Langley 7- by 10-foot high speed tunnel. The angle of attack range was 0 deg to 50 deg and the sideslip angle range was -20 deg to 20 deg. Pitch, roll, and yaw control effectiveness were studied as well as the effects of spoilers. The data are presented without analysis. |
| File Size | 160458767 |
| Page Count | 239 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780005067 |
| Archival Resource Key | ark:/13960/t0qr9mc15 |
| Language | English |
| Publisher Date | 1977-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Subsonic Speed Variable Sweep Wings Static Stability Yaw Sideslip Spoilers Tables Data Longitudinal Control Control Surfaces Pitch Angle of Attack Trailing Edge Flaps Aerodynamic Characteristics Aircraft Configurations Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
