FIELD: transport.
SUBSTANCE: invention relates to thermal protection of aircraft and aerospace equipment. To cool aircraft head-end cooling fluid is supplied to external surface of porous shell towards forward high-temperature gas flow. Axial vibrations with intensity of 0.03 W/m2≤I≤1.2 W/m2 are applied to head-end while cooling fluid injection parameter Re is selected from the range of 1·103≤Re≤1.2·103.
EFFECT: invention is focused on raising cooling efficiency.
2 cl, 4 dwg
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