Using Surface Sensitivity from Mesh Adjoint for Transonic Wing Drag Reduction-Reference-Cited by-同舟云学术

Using Surface Sensitivity from Mesh Adjoint for Transonic Wing Drag Reduction

Published:2017-03 Issue:3 Volume:55 Page:818-831
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Hinchliffe Benjamin¹,Qin Ning¹

Affiliation:

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

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J055319

Reference37 articles.

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

2. FulkerJ. L.AshillP. R.SimmonsM. J. “Study of Simulated Active Control of Shock Waves on an Aerofoil,” Defense Evaluation and Research Agency, TR-93025, Farnborough, Hampshire, England, U.K. May 1993.

3. AshillP. R.FulkerJ. L. “A Novel Technique for Controlling Shock Strength of Laminar-Flow Aerofoil Sections,” German Society for Aeronautics and Astronautics Rept. 92-01-022, Hamburg, Germany, March 1992, pp. 175–175.

4. Investigations on Shock Control Bumps for Infinite Swept Wings

5. Shock control on a swept wing

Cited by 7 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. Vortex-Generating Shock Control Bumps for Robust Drag Reduction at Transonic Speeds;AIAA Journal;2021-10

2. Anisotropic adjoint sensitivity-based mesh movement for industrial applications;Computers & Fluids;2021-05

3. Review of Adaptive Shock Control Systems;Applied Sciences;2021-01-16

4. Using shock control bumps to improve engine intake performance and operability;The Aeronautical Journal;2020-11-23

5. Designing a Shock Control Bump Array for a Transonic Wing–Body Model;AIAA Journal;2018-12