Computational methods for aerodynamic design using numerical optimization
- Peeters, M. F.
- Feb 1, 1983.
- Physical Description:
- 1 electronic document
- Restrictions on Access:
- Unclassified, Unlimited, Publicly available. and Free-to-read Unrestricted online access
- Five methods to increase the computational efficiency of aerodynamic design using numerical optimization, by reducing the computer time required to perform gradient calculations, are examined. The most promising method consists of drastically reducing the size of the computational domain on which aerodynamic calculations are made during gradient calculations. Since a gradient calculation requires the solution of the flow about an airfoil whose geometry was slightly perturbed from a base airfoil, the flow about the base airfoil is used to determine boundary conditions on the reduced computational domain. This method worked well in subcritical flow.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19830010393., Accession ID: 83N18664., NASA-CR-169930., NAS 1.26:169930., and CFDL-TR-83-1.
- No Copyright.
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