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Dynamic stability characteristics in pitch, yaw, and roll of a supercritical-wing research airplane model. [langley 8-foot transonic tunnel tests
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Boyden, R. P. |
| Copyright Year | 1974 |
| Description | The aerodynamic damping in pitch, yaw, and roll and the oscillatory stability in pitch and yaw of a supercritical-wing research airplane model were determined for Mach numbers of 0.25 to 1.20 by using the small-amplitude forced-oscillation technique. The angle-of-attack range was from -2 deg to 20 deg. The effects of the underwing leading-edge vortex generators and the contributions of the wing, vertical tail, and horizontal tail to the appropriate damping and stability were measured. |
| File Size | 53896507 |
| Page Count | 99 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830002753 |
| Archival Resource Key | ark:/13960/t55f3kv4h |
| Language | English |
| Publisher Date | 1974-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aeronautics (general) Aircraft Models Transonic Flight Research Aircraft Dynamic Stability Wind Tunnel Tests Vortex Generators Supercritical Wings Roll Stability Derivatives Stable Oscillations Pitch Inclination Yaw 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 |
