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Effect of wing flexibility on the experimental aerodynamic characteristics of an oblique wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Yee, S. C. Hopkins, E. J. |
| Copyright Year | 1977 |
| Description | A solid-aluminum oblique wing was designed to deflect considerably under load so as to relieve the asymmetric spanwise stalling that is characteristic of this type of wing by creating washout on the trailing wing panel and washin on the leading wing panel. Experimental forces, and pitching, rolling and yawing moments were measured with the wing mounted on a body of revolution. In order to vary the dynamic pressure, measurements were made at several unit Reynolds numbers, and at Mach numbers. The wing was investigated when unswept (at subsonic Mach numbers only) and when swept 45 deg, 50 deg, and 60 deg. The wing was straight tapered in planform, had an aspect ratio of 7.9 (based on the unswept span), and a profile with a maximum thickness of 4 percent chord. The results substantiate the concept that an oblique wing designed with the proper amount of flexibility self relieves itself of asymmetric spanwise stalling and the associated nonlinear moment curves. |
| File Size | 11266697 |
| Page Count | 219 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770014154 |
| Archival Resource Key | ark:/13960/t50g8fx3z |
| Language | English |
| Publisher Date | 1977-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control Boundary Layer Separation Oblique Wings Swept Wings Aluminum Wing Flow Method Tests Aerodynamic Characteristics Wing Loading Flexibility 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 |
