FIELD: aircraft engineering.
SUBSTANCE: device to vary aerodynamic characteristics of hypersonic aircraft comprising airframe, engine, fuel system, planes and control surfaces incorporates bled gas source connected, via sealed pipelines, to permeable porous inserts intended for local gas blow-off into boundary layer of airflow. Cross section area of channels arranged in permeable porous inserts makes 30% to 60% of insert area. Distance between adjacent inserts is 6 to 10 times larger than insert width. Said permeable porous inserts are connected, via sealed pipelines, to low-temperature gas source representing a vortex tube. Proposed method consists in bleeding gas from gas source and feeding it to permeable porous inserts arranged on aircraft surfaces, using above described device, bled gas temperature being other than that of ram airflow.
EFFECT: higher lift.
14 cl, 3 dwg
