A procedure for the optimization of supersonic airfoils is presented. A nonlinear, full-potential solver (NCOREL) is coupled with a numerical optimizer (CONMIN). The NCOREL code is a three-dimensional supersonic marching method, however, only two-dimensional (conical) results are used for the airfoil problem. Each airfoil evaluated in the NCOREL aerodynamic code is composed of a linear combination of user-specified basis airfoils. The weighting factors of the basis airfoils plus the angle of attack form the design variable vector. The inviscid drag coefficient is minimized subject to lift and crossflow Mach number gradient constraints. The optimization strategy is found to be extremely important for the efficient determination of an optimum airfoil.
Supersonic airfoil optimization
1986-01-01
Conference paper
No indication
English
Supersonic airfoil optimization
AIAA | 1986
|Supersonic airfoil optimization
NTRS | 1987
|Supersonic airfoil optimization
AIAA | 1987
|Approach to supersonic airfoil theory
Engineering Index Backfile | 1950
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