Effects of Leading-Edge Vortex Flow on the Roll Damping of Slender Wings
- 1 July 1971
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 8 (7) , 543-547
- https://doi.org/10.2514/3.59135
Abstract
No abstract availableKeywords
This publication has 5 references indexed in Scilit:
- On the singularity method of subsonic lifting- surface theoryPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1969
- Improved calculations of leading-edge separation from slender, thin, delta wingsProceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences, 1968
- Some Remarks on Vortex Drag and its Spanwise Distribution in Incompressible FlowThe Aeronautical Journal, 1968
- A forced-oscillation method for dynamic- stability testingJournal of Aircraft, 1964
- A Study of the Flow Field Associated with a Steadily-Rolling Slender Delta WingJournal of the Royal Aeronautical Society, 1964