俄罗斯空气动力研究所中心学报
每年出版 6 期
ISSN 打印: 1948-2590
ISSN 在线: 1948-2604
ASYMPTOTIC SOLUTION OF THE PROBLEM OF A SUBSONIC GAS FLOW AROUND AN AIRFOIL WITH A LOCAL SUPERSONIC AREA FORMATION
卷 42,
册 2, 2011,
pp. 141-149
DOI: 10.1615/TsAGISciJ.v42.i2.20
摘要
The problem of a transonic flow around an airfoil with a relative thickness of τ << 1 is considered. An asymptotic solution of this problem is obtained for the case of a local supersonic area formation on a smooth airfoil surface. A relative longitudinal dimension of the local supersonic area is proposed to be small, lx << 1. It is shown that in the case when the airfoil surface curvature in the vicinity of the supersonic area is continuous and has order O (τ), a transition of the supersonic flow to the subsonic flow occurs in a continuous way. It is also shown that the shock can arise on the smooth airfoil surface if M∞ − M∞ cr = O (τ2/3).
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