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Effects of differential and symmetrical aileron deflection on the aerodynamic characteristics of an nasa supercritical-wing research airplane model
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Bartlett, D. W. |
| Copyright Year | 1975 |
| Description | An investigation has been conducted in the Langley 8 foot transonic pressure tunnel to determine the effects of differential and symmetrical aileron deflection on the longitudinal and lateral directional aerodynamic characteristics of an 0.087 scale model of an NASA supercritical wing research airplane (TF-8A). Tests were conducted at Mach numbers from 0.25 to 0.99 in order to determine the effects of differential aileron deflection and at Mach numbers of 0.25 and 0.50 to determine the effects of symmetrical aileron (flap) deflection. The angle of attack range for all tests varied from approximately -12 deg to 20 deg. |
| File Size | 9852755 |
| Page Count | 66 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830002803 |
| Archival Resource Key | ark:/13960/t6062bg34 |
| Language | English |
| Publisher Date | 1975-10-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Static Pressure Deflection Wind Tunnel Tests Vortex Generators Ailerons Supercritical Wings Angle of Attack Aerodynamic Characteristics Leading Edges Aerodynamic Loads Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
