Abstract
The problem of reducing the aerodynamic losses through balancing in the supersonic flight regime is considered. An analysis and a comparison of the drag components due to the aerodynamic surface deformation and the balancing weigh distribution is made with reference to the examples of a zero-thickness airfoil and a three-dimensional configuration of an aircraft with a wing of complicated planform. It is shown that minimum values of the aerodynamic drag are achieved as a result of complex optimization including the dead load mass as a varied parameter.
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Original Russian Text © S.A. Takovitskii, 2014, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2014, Vol. 49, No. 2, pp. 113–124.
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Takovitskii, S.A. On the role of a balancing load in the problem of aerodynamic drag minimization in the supersonic flight regime. Fluid Dyn 49, 238–248 (2014). https://doi.org/10.1134/S0015462814020124
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DOI: https://doi.org/10.1134/S0015462814020124