FUSELAGE SHAPE OPTIMIZATION AIMED AT WING-FUSELAGE CONFIGURATION DRAG REDUCTION AT SUPERSONIC SPEEDS

The problem of fuselage shape optimization of the wing-body configuration is considered in the following three formulations. In the first one, the angle of attack is fixed and equal to zero, the wing has a symmetric airfoil, and the fuselage is based on circular cross sections. In the second one, th...

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Bibliographic Details

Published in:	Научный вестник МГТУ ГА
Main Authors:	N. D. Ageev, A. A. Pavlenko
Format:	Article
Language:	Russian
Published:	Moscow State Technical University of Civil Aviation 2017-01-01
Subjects:	аэродинамическое сопротивление сверхзвуковые скорости самолет оптимизация фюзеляж уравнения рейнольдса вычислительная аэродинамика
Online Access:	https://avia.mstuca.ru/jour/article/view/992