DOI

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 оригиналаанглийский
Страницы (с-по)1022-1026
Число страниц5
ЖурналJournal of Engineering Physics and Thermophysics
Том77
Номер выпуска5
DOI
СостояниеОпубликовано - 2004

    Предметные области Scopus

  • Физика конденсатов
  • Технология (все)

ID: 98581465