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Span loadings due to wing twist at transonic and supersonic speeds
| Content Provider | HathiTrust Digital Library |
|---|---|
| Author | Grant, Frederick C Mugler, John P |
| Editor | Frederick C. Grant John P. Mugler |
| Organization | United States. National Advisory Committee for Aeronautics. |
| Description | Two similar tapered sweptback plan forms with the same two spanwise variations of twist have been tested in the Mach number range from 0.8 to 2.0. The test results showed, in general, rather good agreement with theoretical predictions of the incremental span loadings due to twist for zero angle of attack. The measured incremental span loadings due to twist generally diminished with increasing angle of attack through the Mach number range. At a Mach number of 0.9, the incremental loadings progressively vanished from the tip inboard with increasing angle of attack. For the highest angles of attack (about 20 degrees) at Mach number 0.9, there was no difference in the span loadings of the flat and twisted wings. At a higher supersonic speeds, a similar vanishing at the tips of the incremental loading due to twist was starting at the highest angles of attack (near 20 degrees) |
| Volume Number | L57D24A |
| Language | English |
| Publisher | National Advisory Committee for Aeronautics |
| Publisher Date | 1957-01-01 |
| Publisher Place | Washington D.C. |
| Access Restriction | Open |
| Rights License | Items in this record are available as Public Domain, Google-digitized. View the access and use profile at http://www.hathitrust.org/access_use#pd-google. Please see individual items for rights and use statements |
| Subject Keyword | Charts, diagrams, etc Aerodynamics, Supersonic Aerodynamics, Transonic Aerodynamic load Airplanes |
| Content Type | Text |
| Resource Type | Book |
