Investigation of Hysteresis Effects on a Swept Wing/Flap Configuration at High-Lift

Sundaram, S (2001) Investigation of Hysteresis Effects on a Swept Wing/Flap Configuration at High-Lift. Technical Report. National Aerospace Laboratories, Bangalore, India.

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This investigation is on the study of hysterisis effects on a moderately swept wing / flap configuration as commonly used in transport aircraft. The measurements include surface pressure distribution, force measurements using a platform type balance, flqw visualization using tufts and hot-film data to understand the unsteady aspects of flow associated with hysteresis. The configurations studied covered both optimum and non-optimum settings of the gap and overlap between the flap and the main wing. Results indicate features different from that observed in the 20 tests on GA(W) wing section and that the hysteresis loop size was observed to be smaller for the finite wing. It was observed that the trend in the data indicated decrease in the area of hysterisis loop as the slot flow angle is increased contrary to what was observed in 2-D tests. Hystersis was also found to be very sensitive to the slo flow angle which determines its direction with respect to either the wing or the flap chord. The hysteresis loop size diminished when the data was acquired at a much slower rate indicating it to be a quasi-steady event. Both flow patterns from tuft flow visualization and the hot-film fluctuations revealed different flow fields in increasing and decreasing modes of incidence consistent with the observation from the aerodynamic loads.

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Swept Wing;Hysteresis;High-lift;Slotted flap;Balance Measurements
Subjects: AERONAUTICS > Aircraft Design, Testing & Performance
AERONAUTICS > Aerodynamics
Depositing User: Mrs Neetu Chandra
Date Deposited: 08 Jun 2006
Last Modified: 24 May 2010 04:12

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