Numerical Assessment of Leading- and Trailing-Edge Control on a Swept Lambda Wing

Author:

Tormalm Magnus1,Le Roy Jean-François2,Morgand Stephane2

Affiliation:

1. Swedish Defence Research Agency (FOI), SE-16490 Stockholm, Sweden

2. ONERA–The French Aerospace Lab, FR-59045 Lille, France

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Reference22 articles.

1. ElsenaarA.HjelmbergL.BütefischK.A.BanninkW. J. “The International Vortex Flow Experiment,” AGARD CP437, Vol. 1, 1988, pp. 9-1–9-23.

2. HoeijmakersH. W. M. “Modelling and Numerical Simulation of Vortex Flow in Aerodynamics,” AGARD CP-494, 1991, pp. 1-1–1-46.

3. Review of the Second International Vortex Flow Experiment (VFE-2)

4. Numerical investigations on the VFE 2 65-Degree rounded leading edge delta wing using the unstructured DLR-TAU-Code

5. LamarJ.HummelD. “Understanding and Modeling Vortical Flows to Improve the Technology Readiness Level for Military Aircraft,” RTO/AVT, RTO-TR-AVT-113, Final Rept. 2009.

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