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Hinge-Moment, Lift, and Pitching-Moment Characteristics of a Flap-Type Control Surface Having Various Hinge-Line Locations on a 4-Percent-Thick 60 Degree Delta Wing: Transonic Bump Method
| Content Provider | University of North Texas |
|---|---|
| Author | Thompson, Robert F. |
| Organization | Langley Aeronautical Laboratory |
| Description | Report presenting an investigation in the high-speed tunnel to determine the hinge-moment, lift, and pitching-moment characteristics of a 4-percent-thick 60 degree delta wing with a trailing-edge flap-type control. The purpose of this investigation is to determine the ideal aerodynamic balance of a large part of the control force in order to make aircraft easier to control in the event of power failure. |
| File Format | |
| Archival Resource Key | ark:/67531/metadc60184 |
| Language | English |
| Publisher Date | 2019-01-10 |
| Access Restriction | Open |
| Subject Keyword | aerodynamics aircraft stability aircraft wings |
| Content Type | Text |
| Resource Type | Report |