Control Device Studies for Yaw Control without Vertical Tail Plane on a 53° Swept Flying Wing Configuration
Author:
Affiliation:
1. German Aerospace Center (DLR)
Publisher
American Institute of Aeronautics and Astronautics
Link
https://arc.aiaa.org/doi/pdf/10.2514/6.2018-3329
Reference44 articles.
1. Review of the Second International Vortex Flow Experiment (VFE-2)
2. Numerical investigations on the VFE-2 65-degree rounded leading edge delta wing using the unstructured DLR TAU-Code
3. What was Learned from the Numerical Simulations for the VFE-2
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