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TsAGI Science Journal

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ISSN Печать: 1948-2590

ISSN Онлайн: 1948-2604

EXPERIMENTAL INVESTIGATIONS OF WING LIFT CONTROL BY ACTUATORS DISTRIBUTED ON THE WING SURFACE

Том 48, Выпуск 1, 2017, pp. 43-60
DOI: 10.1615/TsAGISciJ.2017020746
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Краткое описание

Comparative studies of diffuser separation control effectiveness by means of different miniature actuators are conducted. Interchangeable plasma actuators, synthetic jet generators, and mechanical vortex generators were mounted on the upper surface of the wing model with NACA 0012 airfoil and 300 mm chord. The lift and drag as functions of the angle of attack were measured by strain gauge balances. The experiment was carried out at a flow velocity of 10-30 m/s in the range of Reynolds numbers determined using the wing chord, 0.27−0.6 × 106, with a turbulent boundary layer on the upper surface of the wing.

ЦИТИРОВАНО В
  1. Karyakin O. M., Nalivaiko A. G., Ustinov M. V., Flaxman Ja. Sh., Separation control on the wing by jet actuators, 1959, 2018. Crossref

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