Vortex-Generating Shock Control Bumps for Robust Drag Reduction at Transonic Speeds-Reference-Cited by-同舟云学术

Vortex-Generating Shock Control Bumps for Robust Drag Reduction at Transonic Speeds

Published:2021-10 Issue:10 Volume:59 Page:3900-3909
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Deng Feng¹,Qin Ning²^ORCID

Affiliation:

1. Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People’s Republic of China

2. University of Sheffield, Sheffield, England S1 3JD, United Kingdom

Funder

University of Sheffield Proof of Concept Fund

National Natural Science Foundation of China

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.J060528

Reference41 articles.

1. Shock Wave Drag Reduction

2. StanewskyE.DéleryJ.FulkerJ.GeißlerW., Synopsis of the Project EUROSHOCK. Notes on Numerical Fluid Mechanics: EUROSHOCK—Drag Reduction by Passive Shock Control, Results of the Project EUROSHOCK, Vol. 56, Friedr. Vieweg & Sohn Verlagsgesellschaft mbH, Braunschweig/Wiesbaden, 1997, pp. 1–87.

3. StanewskyE.DéleryJ.FulkerJ.De MatteisP., Synopsis of the Project EUROSHOCK II. Notes on Numerical Fluid Mechanics and Multidisciplinary Design: Drag Reduction by Shock and Boundary Layer Control-Results of the Project EUROSHOCK II, Vol. 80, Springer–Verlag, Berlin, 2002, pp. 1–124.

4. TaiT. C. “Theoretical Aspects of Dromedaryfoil,” David W. Taylor Naval Ship Research and Development Center TR 770104, Bethesda, MD, 1977.

5. Transonic characteristics of a humped airfoil

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