![]() Experiments in Fluids, 25, 108–117 (1998)īrodeur, R., van Dam, C.P.: Transition prediction for a twodimensional Navier-Stokes solver applied to wind-turbine airfoils. Lee, T., Basu, S.: Measurement of unsteady boundary layer developed on an oscillating airfoil using multiple hot-film sensors. Schreck, S., Faller, W.E., Helin, H.E.: Pitch rate and Reynolds number effects on unsteady boundary-layer transition and separation. AIAA-96-0035, 34th Aerospace Sciences Meeting and Exhibit, Reno, NV (1996) Pascazio, M., Autric, J.M., Favier, D., et al.: Unsteady boundary-layer measurement on oscillating airfoils, transition and separation phenomena in pitching motion. 43rd AIAA Aerospace Sciences Meeting and Exhibit (2005) D., Tangler: Wind turbine post-stall airfoil performance characteristics guidelines for blade-element momentum methods. #BOUNDARY LAYER AIRFOIL SKIN#By increasing the reduced frequency, the boundary layer transition was promoted to the upstroke portion of the equivalent angle of attack, but the quasi skin friction coefficient was decreased. The mean angle of attack and the oscillating parameters significantly affected the state of the boundary layer. For the dynamic tests, earlier transition occurred with increasing rather than decreasing effective angle of attack. By increasing the angle of attack, disturbances and the transition location moved toward the leading edge. For the static tests, boundary layer transition occurred through a laminar separation bubble. The results of the quasi-wall-shear stress as well as the boundary layer velocity profiles provided important information about the state of the boundary layer over the suction surface of the airfoil in both static and dynamic cases. The experiments were conducted at Reynolds numbers of 0.42×10 6 to 0.84 × 10 6 and the reduced frequency was varied from 0.01 to 0.11. The wind tunnel measurements involved surfacemounted hot-film sensors and boundary-layer rake. It specifically deals with the effect of plunging oscillation on the laminar/turbulent characteristics of the boundary layer. This is an experimental study on the boundary layer over an airfoil under steady and unsteady conditions. ![]()
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