Publicou 6 edições por ano
ISSN Imprimir: 1948-2590
ISSN On-line: 1948-2604
EXPERIMENTAL INVESTIGATION OF STATIC PRESSURES ON THE UPPER SURFACE OF A PASSENGER AIRCRAFT MODEL AT QUASI-STEP-WISE VARIATIONS OF THE PITCH ANGLE IN SEPARATION FLOW REGIMES
RESUMO
Transitions of static pressure on the upper surface of the wing and horizontal tail during fast displacement of the model from small to high angles of attack are obtained. The behavior of the transitions on the wing and on the horizontal tail is found to be significantly different. The process of relaxation of loads is revealed to be exponential and characterized by dimensionless time constants T ≈ 4 − 6 for the wing and, accordingly, T ≈ 13 − 14 for the horizontal tail.
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Chasovnikov E. A., Mathematical modeling of self-induced oscillations of a segmental-conical body with free movement in the pitch angle, INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2020), 2351, 2021. Crossref