Sonic Boom Reduction Using an Adjoint Method for Wing-Body Configurations in Supersonic Flow
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Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2002-5547
Reference8 articles.
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3. 3S. Komadina, A. Drake, and S. Bruner Development of a Quiet Supersonic Aircraft with Technology Applications to Military and Civil Aircraft. AIAA 2002-0519, 40th Aerospace Sciences Meeting and Exibit, Reno, Nevada, January 2002.
4. 4C. Farhat, K. Maute, B. Argrow, and M. Nikbay A Shape Optimization Methodology for Reducing the Sonic Boom Initial Pressure Rise. AIAA 2002-0145, 40th Aerospace Sciences Meeting and Exibit, Reno, Nevada, January 2002.
5. 5S. Nadarajah and A. Jameson. A Comparison of the Continuous and Discrete Adjoint Approach to Automatic Aerodynamic Optimization. AIAA 00-0667, AIAA 38th. Aerospace Sciences Meeting and Exhibit, Reno, NV, January 2000.
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