Titlebook: Low Reynolds Number Aerodynamics; Proceedings of the C Thomas J. Mueller Conference proceedings 1989 Springer-Verlag Berlin, Heidelberg 198

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Study of Low-Reynolds Number Separated Flow Past the Wortmann FX 63-137 Airfoil, simulation (DNS) methodology is used to obtain flow results at Re = 1,000 with α. varying from ?5° to 10°; simulations are also performed at α. = 0° with Re = 10,000 and 100,000 without any turbulence model.

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Unsteady Aerodynamics of Wortmann FX63-137 Airfoil at Low Reynolds Numbers, frequencies tested are quite similar. The ensemble averaged profiles for . = 0.15 suggest that the unsteady boundary layer tends to be more attached when the free stream velocity is minimum. Data show that this effect is less pronounced at . = 2.0.

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A Method to Determine the Performance of Low-Reynolds-Number Airfoils under Off-Design Unsteady Frere work will include application of this technique to two state-of-the art airfoils, the ASM-LRN-010 (see Reference [1]) and Wortmann FX63–137 airfoil sections with chord Reynolds numbers of 250,000 and 500,000 and operating under light dynamic stall conditions.

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Low Reynolds Number Airfoil Design and Wind Tunnel Testing at Princeton University,ssed and verified experimentally. Several of the new airfoils show significant performance improvements over previous airfoils. Boundary layer trips were also investigated as a means of reducing drag. Several types of trips were compared (zig-zag trips, bump tape, blowing, and two-dimensional trips)

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The Instability of Two-Dimensional Laminar Separation,ynolds number and the pressure gradient. The vortex shedding was due to the inviscid instability of the separated laminar shear layer..When the results were time-averaged, the unsteady separation produced a pressure gradient and streamline pattern similar to those found in laminar separation experim

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Experimental aerodynamic characteristics of the airfoils LA 5055 and DU 86-084/18 at low Reynolds n drag producing laminar separation bubbles were present, and drag reductions up to 33% were measured by applying a zig-zag tape turbulator for transition control. The maximum lift coefficient, being governed by the Stratford limiting pressure distribution, could be raised by 38% with semi triangular

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A Computationally Efficient Modelling of Laminar Separation Bubbles,dary-layer properties at that point as the initial conditions for the turbulent boundary-layer calculations usually underpredict the drag. Thus, to successfully determine the increase in drag on an airfoil due to separation bubbles, it is necessary to accurately model the development of the boundary