Numerical lifting line theory applied to drooped leading-edge wings below and above stall
- 1 December 1980
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Aircraft
- Vol. 17 (12) , 898-904
- https://doi.org/10.2514/3.44690
Abstract
No abstract availableKeywords
This publication has 8 references indexed in Scilit:
- Flowfield Model for a Rectangular Planform Wing beyond StallAIAA Journal, 1980
- The effects of leading edge modifications on the post-stall characteristics of wingsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1980
- The effects of configuration changes on spin and recovery characteristics of a low-wing general aviation research airplanePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1979
- Exploratory study of the influence of wing leading-edge modifications on the spin characteristics of a low-wing single-engine general aviation airplanePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1979
- Historical Overview of Stall/Spin Characteristics of General Aviation AircraftJournal of Aircraft, 1979
- A method for localizing wing flow separation at stall to alleviate spin entry tendenciesPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1978
- Some Recent Developments in Airfoil TheoryJournal of the Aeronautical Sciences, 1956
- A new treatment of the lifting-line wing theory, with applications to rigid and elastic wingsQuarterly of Applied Mathematics, 1948