FIELD: aircraft engineering.
SUBSTANCE: invention relates to aerodynamics of supersonic and transonic aircrafts. Method of supersonic flow braking consists in creation of compression shock waves, moving relative to streamlined surface in direction of flow, with speed values smaller than difference of flow speeds and sound speed in front of compression shock waves values. Compression shock waves movement is performed by creation of transverse waves travelling in flow direction in flow at streamlined surface. Transverse travelling waves are created by means of transversal progressive deformations of streamlined surface outline or by periodic, alternating air suction and blow-out from streamlined surface sections with suction and blow-out phases shift between adjacent sections of streamlined surface.
EFFECT: invention is aimed at reducing of total pressure losses.
3 cl, 4 dwg
