Using Mesh Adjoint for Shock Bump Deployment and Optimisation on Transonic Wings-Reference-Cited by-同舟云学术

Using Mesh Adjoint for Shock Bump Deployment and Optimisation on Transonic Wings

Published:2015-01-03 Issue: Volume: Page:
ISSN:
Container-title:53rd AIAA Aerospace Sciences Meeting
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Author:

Zhu Feng¹,Qin Ning¹

Affiliation:

1. University of Sheffield

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2015-1488

Reference27 articles.

1. 1Fulker, J. L., Ashill, P. R. & Simmons, M. J. Study of simulated active control of shock waves on an aerofoil Technical Report 93025. DERA May 1993.

2. 3Zhu, Y. P. 2000. Computational Study of Shock Control at Transonic Speed. PhD Thesis,Cranfield University.

3. 4Lutz, T., Kutzbach, M. & Wagner, S. Investigations on shock control bumps for infinite swept wings. AIAA2004-2702

4. Shock control on a swept wing

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