FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering. Proposed method comprises changing the airflow direction from oncoming to radial efflux relative to aircraft. Oncoming airflow is directed through gastight porous inserts isolated and separated from aircraft airframe arranged in symmetry relative to aircraft nose lengthwise axis. Said inserts are heated simultaneously or in turns to develop symmetric or asymmetric effects on oncoming airflow. Gastight porous inserts are heated by mean of glowing electric charge, or catalytic combustion of combustible mix, or electric ohmic heater. Said inserts are heat- and electrically insulated, or heat isolated from each other and from aircraft airframe.
EFFECT: accelerated control over overflow.
4 cl, 3 dwg
