Effect of leading-edge cross-sectional geometry on slender wing unsteady aerodynamics
- 6 January 1992
- proceedings article
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 4 references indexed in Scilit:
- Control of vortical lift on delta wings by tangential leading-edge blowingJournal of Aircraft, 1988
- Dynamic support interference in high-alpha testingJournal of Aircraft, 1986
- Errata: Unsteady Aerodynamics of Slender Delta Wings at Large Angles of AttackJournal of Aircraft, 1977
- Predictions of vortex-lift characteristics by a leading-edge suctionanalogyJournal of Aircraft, 1971