Abstract
By successive conformal transformations, the flow past a semicircular cone has been investigated with the help of Mangler and Smith's mathematical model of the flow past a slender delta wing with zero thickness. The thickness effect has thus been directly determined in the case of flow past slender delta wing and the lift and drag coefficients have been calculated in terms of dimensionless angle of incidence. Further, the lift coefficient has been compared with the semi-empirical result of Bergsen and Porter.
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