engleski

Analysis of supersonic flow in Oswatitsch inlet configuration

The aim of this work is a study of the flow parameters relevant for the Oswatitsch intake configuration. Geometry of the cone and inlet are equivalent to those on MiG-21bis fighter aircraft. Supersonic flow parameters for a channeled cone were studied at two different operational Mach numbers. Center body cone is movable along longitudinal axis and analysis is focused on specific positions for supersonic flight regimes. To study the problem, numerical model of axisymmetric two-dimensional Euler flow is applied.

Oswatitsch inlet; supersonic flow; numerical model of axisymmetric flow

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