An Examination of the Effect of Reynolds Number on Airfoil Performance

Abstract

The standard of living throughout the world has increased dramatically over the last 30 years and is projected to continue to rise. This growth leads to an increased demand on conventional energy sources, such as fossil fuels. However, these are finite resources. Thus, there is an increasing demand for alternative energy sources, such as wind energy. Much of current wind turbine research focuses on large-scale (>1 MW), technologically-complex wind turbines installed in areas of high average wind speed (>20 mph). An alternative approach is to focus on small-scale (1–10kW), technologically-simple wind turbines built to produce power in low wind regions. While these turbines may not be as efficient as the large-scale systems, they require less industrial support and a less complicated electrical grid since the power can be generated at the consumer’s location. To pursue this approach, a design methodology for small-scale wind turbines must be developed and validated. This paper addresses one element of this methodology, airfoil performance prediction. In the traditional design process, an airfoil is selected and published lift and drag curves are used to optimize the blade twist and predict performance. These published curves are typically generated using either experimental testing or a numeric code, such as PROFIL (the Eppler Airfoil Design and Analysis Code) or XFOIL. However, the published curves often represent performance over a different range of Reynolds numbers than the actual design conditions. Wind turbines are typically designed from 2-D airfoil data, so having accurate airfoil data for the design conditions is critical. This is particularly crucial for small-scale, fixed-pitched wind turbines, which typically operate at low Reynolds numbers (<500,000) where airfoil performance can change significantly with Reynolds number. From a simple 2-D approach, the ideal operating condition for an airfoil to produce torque is the angle of attack at which lift is maximized and drag is minimized, so prediction of this angle will be compared using experimental and simulated data. Theoretical simulations in XFOIL of the E387 airfoil, designed for low Reynolds numbers, suggest that this optimum angle for design is Reynolds number dependent, predicting a difference of 2.25° over a Reynolds number range of 460,000 to 60,000. Published experimental data for the E387 airfoil demonstrate a difference of 2.0° over this same Reynolds number range. Data taken in the Baylor University Subsonic Wind Tunnel for the S823 airfoil shows a similar trend. This paper examines data for the E387 and S823 airfoils at low Reynolds numbers (75,000, 150,000, and 200,000 for the S823) and compares the experimental data with XFOIL predictions and published PROFIL predictions.

Blade element momentum theory extended to model low Reynolds number propeller performance

“…The importance of appropriate aerofoil data for low Reynolds number applications has been well established in the analysis of small wind turbines (24,(30)(31)(32) , and the same holds true for small propellers (9,13,23) . When using blade element analysis methods, aerodynamic data is commonly obtained for a single Reynolds number, taken at 70-75% of the radius (17,33,34) ;…”

Numerical Analysis of NACA 6409 and Eppler 423 Airfoils

“…It has been reported that increased lift coefficients in parallel with the increase in turbulence levels. Burdet et al [14] used PROFIL (Eppler Airfoil Design and Analysis Code) and XFOIL software to examine the effect of Reynolds number on the E387 wing profile. It is argued that the design angle of attack depends on the Reynolds number and that the PROFIL data lead to a difference of more than 3 degrees compared to the experimental data for wind turbine blade design.…”

Geometrical Design of a Rotor Blade for a Small Scale Horizontal Axis Wind Turbine

“…Results showed that the airfoil with 30% varying thickness demonstrated better aerodynamic characteristics compared to the baseline airfoil. Burdett et al [16] extensively validated the aerodynamic results of S823 and E387 airfoils invoked from PROFIL and XFOIL numerical codes with the experimental data. The research work shows that the design angle of attack estimated by numerical simulations were around 2.5% lesser than the experimental techniques.…”