Aerodynamic design via control theory
 Antony Jameson
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The purpose of the last three sections is to demonstrate by representative examples that control theory can be used to formulate computationally feasible procedures for aerodynamic design. The cost of each iteration is of the same order as two flow solutions, since the adjoint equation is of comparable complexity to the flow equation, and the remaining auxiliary equations could be solved quite inexpensively. Provided, therefore, that one can afford the cost of a moderate number of flow solutions, procedures of this type can be used to derive improved designs. The approach is quite general, not limited to particular choices of the coordinate transformation or cost function, which might in fact contain measures of other criteria of performance such as lift and drag. For the sake of simplicity certain complicating factors, such as the need to include a special term in the mapping function to generate a corner at the trailing edge, have been suppressed from the present analysis. Also it remains to explore the numerical implementation of the design procedures proposed in this paper.
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 Title
 Aerodynamic design via control theory
 Journal

Journal of Scientific Computing
Volume 3, Issue 3 , pp 233260
 Cover Date
 19880901
 DOI
 10.1007/BF01061285
 Print ISSN
 08857474
 Online ISSN
 15737691
 Publisher
 Kluwer Academic PublishersPlenum Publishers
 Additional Links
 Topics
 Keywords

 Computational aerodynamics
 transonic flow
 inverse problem
 wing design
 optimization
 Industry Sectors
 Authors

 Antony Jameson ^{(1)}
 Author Affiliations

 1. Department of Mechanical and Aerospace Engineering, Princeton University, 08544, Princeton, New Jersey