Recent applications of numerical optimization to the design of advanced airfoils for transonic aircraft have shown that low-drag sections can be developed for a given design Mach number without an accompanying drag increase at lower Mach numbers. This is achieved by imposing a constraint in the drag coefficient at an off-design Mach number while the drag at the design Mach number is the objective function. Such a procedure doubles the computation time over that for single design-point problems, but the final result is worth the increased cost of computation, The ability to treat such multiple designpoint problems by numerical optimization has been enhanced by the development of improved airfoil shape functions. Such functions permit a considerable increase in the range of profiles attainable during the optimization process.
Application of numerical optimization to the design of supercritical airfoils without drag-creep
Numerische Optimierung bei der Konstruktion superkritischer Tragflaechen ohne Stroemungswiderstand
SAE-Papers ; 1-11
1977
11 Seiten, 11 Bilder, 13 Quellen
Conference paper
English
Application of Numerical Optimization to the Design of Supercritical Airfoils without Drag-Creep
SAE Technical Papers | 1977
|Numerical optimization design of transonic airfoils
TIBKAT | 1987
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