An application of numerical optimization to the design of advanced airfoils for transonic aircraft showed 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 on the drag coefficient at an off-design Mach number while minimizing the drag coefficient at the design Mach number. This multiple design-point numerical optimization has been implemented with the use of airfoil shape functions which permit a wide range of attainable profiles during the optimization process. Analytical data for the starting airfoil shape, a single design-point optimized shape, and a double design-point optimized shape are presented. Experimental data obtained in the NASA Ames two-by two-foot wind tunnel are also presented and discussed.
Application of numerical optimization to the design of advanced supercritical airfoils
01.01.1979
Aufsatz (Konferenz)
Keine Angabe
Englisch
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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