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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

Volume 42, Edição 6, 2011, pp. 845-851
DOI: 10.1615/TsAGISciJ.2012004705
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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.

CITADO POR
  1. 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

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