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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
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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 = O2/3).

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