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Static longitudinal aerodynamic characteristics of a model with a modified 17 percent thick supercritical wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ferris, J. C. |
| Copyright Year | 1975 |
| Description | The static longitudinal stability characteristics of a 0.09 scale model of an airplane with a modified 17 percent thick supercritical wing were investigated. Modifications were made to the wing to reduce a gradual buildup of boundary layer shock loss preceding drag divergence (drag creep) noted in an earlier investigation. The longitudinal aerodynamic characteristics were determined over a Mach number range from 0.30 to 0.76 at angles of attack that generally provided a lift coefficient range from 0 to buffet onset. Results indicate that the modifications to the airfoil essentially eliminated the drag creep associated with the airfoil that occurs between the critical Mach number and the drag divergence Mach number. |
| File Size | 10183499 |
| Page Count | 40 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830002811 |
| Archival Resource Key | ark:/13960/t2d843p8d |
| Language | English |
| Publisher Date | 1975-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aircraft Models Thickness Aerodynamic Drag Static Stability Wind Tunnel Tests Supercritical Wings Wing Profiles Angle of Attack Aerodynamic Stability Longitudinal Stability Mach Number Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
