ON THE EFFECT OF THE INCIDENT MACH’S WAVE ON THE PULSATION LEVEL IN BOUNDARY LAYER OF THE PLANE DELTA WING
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Keywords:
supersonic flow, experimental investigations, wind tunnel, delta wing with blunted leading edges, laminarturbulent transition, hot-wire anemometer.
УДК 532.526
ON THE EFFECT OF THE INCIDENT MACH’S WAVE ON THE PULSATION LEVEL IN BOUNDARY LAYER OF THE PLANE DELTA WING
The material was received by the Editorial Board: 29.11.2013
The experimental results of high level fluctuation excitation by external Mach’s wave in the boundary layer of delta wing model with blunt leading edges at Mach numbers M = 2, 2.5, 4 are presented. The exitation areas and mass flow pulsation levels in the conditions of subsonic, sonic and supersonic leading edges have been defined. It was found that the maximum value of the pulsations is 12–15 % and varies only slightly from the flow conditions around of the delta wing. Keywords:
supersonic flow, experimental investigations, wind tunnel, delta wing with blunted leading edges, laminarturbulent transition, hot-wire anemometer.
УДК 532.526
ON THE EFFECT OF THE INCIDENT MACH’S WAVE ON THE PULSATION LEVEL IN BOUNDARY LAYER OF THE PLANE DELTA WING References: Vaganov A. V., Yermolaev Yu. G., Kolosov G. L., Kosinov A. D., Panina A. V., Semionov N. V. ON THE EFFECT OF THE INCIDENT MACH’S WAVE ON THE PULSATION LEVEL IN BOUNDARY LAYER OF THE PLANE DELTA WING . Vestnik NSU. Series: Physics. 2014, vol. 9, no. 1. P. 29–38 (in Russ.). DOI: 10.54362/1818-7919-2014-9-1-29-38