FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering. Proposed method comprises suction of flow portion via surface perforation into chamber above it at flow section behind the shock wave. Lengthwise vortex bundles are created nearby flow surface ahead of shock wave by forcing out some transverse flows from surface channels communicated via channel with chamber above said perforated surface. Said transverse jets are forced ahead of shock wave at angle of 30-60 degrees to flow surface across flow direction.
EFFECT: lower drag.
2 cl, 4 dwg
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