Slender wings with leading-edge vortex separation - A challenge for panel methods and Euler solvers-Reference-Cited by-同舟云学术

Slender wings with leading-edge vortex separation - A challenge for panel methods and Euler solvers

Published:1984-10 Issue:10 Volume:21 Page:751-759
ISSN:0021-8669
Container-title:Journal of Aircraft
language:en
Short-container-title:Journal of Aircraft

Author:

Hitzel Stephan M.¹,Schmidt Wolfgang¹

Affiliation:

1. Dornier GmbH, Friedrichshafen, Federal Republic of Germany

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/3.45038

Reference35 articles.

1. Hummel D. "On the Vortex Formation over a Slender Wing at Large Angles of Incidence "AGARD CP 247 High Angle of Attack Aerodynamics 1978, pp 15/115/17

2. Strömungsvorgänge an Platten und profilierten Körpern bei kleinen Spannweiten

3. Wilson, H. A. and Lovell, G. C. "Full Scale Investigations of the Maximum Lift and Flow Characteristics of an Airplane Having Approximately Triangular Plan Form," NACAL6K20,1946.

Cited by 45 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Historical development and use of CFD for separated flow simulations relevant to military aircraft;Aerospace Science and Technology;2021-10

2. Flow criticality governs leading-edge-vortex initiation on finite wings in unsteady flow;Journal of Fluid Mechanics;2021-01-08

3. Small Aspect-Ratio Delta-Type Wing Flow;Separated and Vortical Flow in Aircraft Wing Aerodynamics;2020-10-05

4. Vortex-Sheet Representation of Leading-Edge Vortex Shedding from Finite Wings;Journal of Aircraft;2019-07

5. Physics of vortical flows;Journal of Aircraft;1992-09