Three-Dimensional Solution of Flows over Wings with Leading-Edge Vortex Separation
- 1 April 1976
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 14 (4), 519-525
- https://doi.org/10.2514/3.61391
Abstract
No abstract availableThis publication has 3 references indexed in Scilit:
- Advanced panel-type influence coefficient methods applied to subsonic flowsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1975
- Predictions of vortex-lift characteristics by a leading-edge suctionanalogyJournal of Aircraft, 1971
- A theory of the flow past a slender delta wing with leading edge separationProceedings of the Royal Society of London. Series A. Mathematical and Physical Sciences, 1959