Результаты исследований: Научные публикации в периодических изданиях › статья › Рецензирование
Inviscid transonic flow over the DSMA523a and Whitcomb airfoils and an airfoil described by a simple algebraic formula has been investigated numerically. The dependence of the flow structure and the lift coefficient on the freestream Mach number Moo and the angle of attack (X has been studied. The values of M∞ and a at which steady-state flow becomes unstable have been revealed. The relationship between the flow nonuniqueness occurring in certain ranges of variation of M∞ and α and the instability has been analyzed.
Язык оригинала | английский |
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Страницы (с-по) | 1022-1026 |
Число страниц | 5 |
Журнал | Journal of Engineering Physics and Thermophysics |
Том | 77 |
Номер выпуска | 5 |
DOI | |
Состояние | Опубликовано - 2004 |
ID: 98581465