Iterative Design Techniques for Thick Cambered Wings in Subcritical Flow,

The authors method for computing steady, inviscid, subcritical flow past a thick cambered wing is extended to design applications. Four problems are considered 1 given thickness and doublet first-order loading distributions 2 given thickness and upper-surface pressure distributions 3 given loading and upper-surface pressure distributions 4 a hybrid of 2 and 3 in which the thickness is specified everywhere except near the root, and is determined near the root when the doublet distribution is constrained to exhibit spanwise invariance in that region. Convergence for the first problem is excellent. For all problems, good convergence is obtained outboard. For the single case reported of the second problem, convergence was secured near the root but cannot yet be guaranteed. Near the root, slow convergence was obtained for the third problem, rather better convergence for the fourth problem. This hybrid option is tentatively recommended. Author