Abstract
Flow characteristics of an S826 airfoil at different Reynolds numbers, ranging from 40,000–400,000 (based on airfoil chord length) and angles of attack from −10–25 degrees are thoroughly investigated in a low-speed wind tunnel. The airfoil’s lift and drag polars are first measured, and with a focus on pitching the airfoil in upstroke and downstroke orders, static stall hysteresis is identified in selected experiments at Reynolds numbers below 100,000 near the stall angle and subsequently investigated. Experiments using wire-generated free stream turbulence are conducted, and the hysteresis effects are shown to disappear when introducing a free stream turbulence of less than 2.5%. Further, spanwise flow is detected by comparing lift and drag values measured using both surface pressure integration at one cross section as well as integral force gauge measurement, and the surface oil flow visualization technique is subsequently used to study the 3D flow topologies formed on the airfoil. The formation of distinct stall cells on the suction side of the airfoil is observed at Reynolds numbers above 100,000 near the stall angle. By repeating the experiments, stall cells are proven to be reproduceable, although the identical geometries are necessarily not retained in abscence of surface impurities such as tapes. The effect of disturbances on the stall cells is investigated by utilizing roughness elements on the airfoil surface, and it is found that while such disturbances tend to change the shape of the stall cells, they do not contribute to the creation, nor destruction of the cells. Polar and visualisation measurements are also used to study flow separation, and it is observed that the separation location, as well as the laminar separation bubble, moves towards the leading edge when increasing the angle of attack.
Highlights
The aerodynamics at low Reynolds numbers is of high relevance for the design of small domestic wind turbines with rotor diameters ranging from 2–7 m, corresponding to rated generator capacities of 0.3–10 kW
It can be seen that the lift and drag coefficients corresponding to Re = 40,000 result in different values for increasing and decreasing the angle of attack
This is due to so-called static stall hysteresis
Summary
The aerodynamics at low Reynolds numbers is of high relevance for the design of small domestic wind turbines with rotor diameters ranging from 2–7 m, corresponding to rated generator capacities of 0.3–10 kW. Recent wind turbine rotor experiments and CFD investigations [2,24] have suggested that the airfoil investigated in the current study exhibits a complex flow behavior at the operating Reynolds numbers in the range from 40,000–200,000. Version May 21, 2018 submitted to Energies wind tunnel measurements in order to provide a deeper understanding of the fluid flow phenomena and the mechanisms in which stall cells are formed With this in mind, the structure of this article is as are formed. The wake-rake, consisting of 32 measuring points, is the inlet section of the wind tunnel to measure the reference pressure and subsequently the free-stream mounted x = 1.6c downstream of the airfoil and at a height z = 2.1c of the test object.
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