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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| Main Authors: | , |
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| Format: | Article |
| Language: | Russian |
| Published: |
Moscow State Technical University of Civil Aviation
2017-01-01
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| Series: | Научный вестник МГТУ ГА |
| Subjects: | |
| Online Access: | https://avia.mstuca.ru/jour/article/view/992 |
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