Abstract
A theoretical approach to investigating the flow over strake-slender-wing combinations is presented. The method developed consists of a modification of a well-known slender-wing-theory model together with the development of an approximate local solution in the kink region. This enables us to take care of the leading-edge discontinuity. The theoretical results predicted by the present method permit a rapid, qualitative investigation of the parameters that influence the vortex-flow patterns and the aerodynamic coefficients, within certain limitations and a comparison of configurations. Quantitatively, the calculation results in an overprediction of the forces. This trend is typical of slender-wing methods. The method could be readily extended to deal with the case of a strakeslender-wing arrangement mounted on a slender fuselage.
Published Version
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