The slenderness assumption of Munk (1924) and Jones (1946), made over and above that of linearization, has often been used to get closed form analytical solutions for wings, bodies, and their combinations. Here, simple expressions are obtained for the aerodynamic characteristics of a slender delta wing, exhibiting an even-order polynomial twist distribution in the spanwise coordinate. Carafoli (1956) derived an integral equation which relates the twist distribution to the pressure distribution. Linearized theory predicts two kinds of solution: one in which a leading edge singularity appears, and the other in which the leading edge experiences zero load.
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