The airfoil performance and flow structures of a model with a NACA 633-018 airfoil section is studied experimentally in a wind tunnel. The pressure distributions, boundary layer profiles, and the corresponding aerodynamic properties are measured at various angles of attack, and at the Reynolds number range from 300000 to 750000 based on the wing chord. Hot-wire anemometry and smoke wire technique are also applied for performing the flow measurements and visualization, respectively. Data indicate that the flow field over the airfoil appears to be transitional in the operating range. The flow starts to be separated from the airfoil surface after the pressure gradient becomes positive and, then, reattached to form a laminar separation bubble. The spectral analysis of the fluctuating velocities in the recirculating region also clearly ascertains the existence of the prevailing vortices. Meanwhile, the hysteresis phenomenon in the non-linear range of the lift curves with angle of attack is significantly noted, especially in the low Reynolds number range.
Experimental studies of airfoil performance and flow structures on a low Reynolds number airfoil
Experimentelle Untersuchung von Tragfluegeln und von Stroemungsstrukturen an mit niedrigen Reynoldszahlen umstroemten Tragflaechen
AIAA-Papers ; Jul ; 1-9
1987
9 Seiten, 25 Bilder, 16 Quellen
Aufsatz (Konferenz)
Englisch
Low Reynolds Number Airfoil Design
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