3 component LDV for near wall measurements on a multi-element high lift airfoil configuration

Seelhorst, U.; Bütefisch, K.-A.; Weiland, M.

doi:10.1109/iciasf.1995.519486

Cited by 1 publication

(1 citation statement)

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“…Several experimental studies 5−9 on two-dimensional high-lift configurations have been reported, and hot-wire anemometry has been utilized to obtain mean and turbulence data. There have also been some attempts 10 to measure the flowfield using laser velocimetry. The use of two-dimensional particle image velocimetry (PIV) is relatively recent, 11 but very attractive from the point of view of documenting the velocity field in a given plane including flow reversal.…”

Section: Introductionmentioning

confidence: 99%

Hysteresis and Broad Flow Features on a Swept Wing at High Lift

Venkatakrishnan

Sundaram

Viswanath

2006

Journal of Aircraft

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Experiments have been performed at low speeds documenting certain broad aspects of hysteresis on a mildly swept wing under high-lift conditions. Aerodynamic load measurements were carried out at two values of incidence, 10.5 and 15.5 deg, and flap deflections of 20 and 30 deg, essentially under quasi-steady conditions. Two-dimensional particle image velocimetry (PIV) was utilized to measure the mean velocity vector field in the rear part of the wing and flap. These velocity measurements have revealed the complex nature of separated flows on the wing and flap. Also, in general, the slot flow angle determined by geometric considerations is very different from those actually inferred from PIV measurements. Nomenclature A w = wing area, 0.3 m 2 C L = lift coefficient, [lift force/(freestream dynamic head × wing area)] C D = drag coefficient, [drag force/(freestream dynamic head × wing area)] q ∞ = freestream dynamic head U = local velocity, m/s U ∞ = freestream velocity, m/s α = angle of incidence, deg δ f = flap deflection, deg

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Section: Introductionmentioning

confidence: 99%