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Lateral Stability Characteristics at Low Lift Between Mach Numbers of 0.85 and 1.15 of a Rocket-Propelled Model of a Supersonic Airplane Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degrees Sweepback
| Content Provider | University of North Texas |
|---|---|
| Author | D'Aiutolo, Charles T. Henning, Allen B. |
| Organization | Langley Aeronautical Laboratory |
| Description | Report presenting testing of a model of a supersonic airplane configuration with a 40 degree sweptback wing with circular-arc sections at Mach numbers 0.85 and 1.15 to obtain lateral stability data at low lift and to evaluate the test and analysis technique. Results regarding time history, trim characteristics, amplitude ratio and phase of rolling angular acceleration to angle of sideslip, sideslip derivatives, moment derivatives due to yawing, and a comparison of present data with previously obtained data are provided. |
| File Format | |
| Archival Resource Key | ark:/67531/metadc61131 |
| Language | English |
| Publisher Date | 2019-01-14 |
| Access Restriction | Open |
| Subject Keyword | aircraft stability aircraft control aircraft testing |
| Content Type | Text |
| Resource Type | Report |