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Piloted-simulation study of effects of vortex flaps on low-speed handling qualities of a delta-wing airplane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wunschel, Alfred J. Brandon, Jay M. Brown, Philip W. |
| Copyright Year | 1987 |
| Description | A piloted-simulation study was conducted to investigate the effects of vortex flaps on low-speed handling qualities of a delta-wing airplane. The simulation math model was developed from wind tunnel tests of a 0.15 scale model of the F-106B airplane. Pilot evaluations were conducted using a six-degree-of-freedom motion base simulator. The results of the investigation showed that the reduced static longitudinal stability caused by the vortex flaps significantly degraded handling qualities in the approach-to-landing task. Acceptable handling qualities could be achieved by limiting the aft center-of-gravity location, consequently reducing the operational envelope of the airplane. Further improvement were possible by modifying the flight control force-feel system to reduce pitch-control sensitivity. |
| File Size | 5295265 |
| Page Count | 38 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870017489 |
| Archival Resource Key | ark:/13960/t3615xg62 |
| Language | English |
| Publisher Date | 1987-09-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Degrees of Freedom Pilots Personnel Low Speed F-106 Aircraft Flight Control Longitudinal Stability Flight Envelopes Pitch Inclination Sensitivity Center of Gravity Delta Wings Vortex Flaps Controllability Mathematical Models Flight Simulation 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 |
