Application of numerical optimization to the design of supercritical airfoils without drag-creepRecent 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 on 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 design-point 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.
Document ID
19770054209
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hicks, R. M. (NASA Ames Research Center Moffett Field, CA, United States)
Vanderplaats, G. N. (NASA Ames Research Center Moffett Field, Calif., United States)