On the surface of the central part, there are 36 small holes that are distributed strategically across the top and bottom of the airfoil. ![]() The central part is mostly hollow, containing two slots which a metal bar acting as a spar runs through to connect the three parts. The case is a two-dimensional airfoil located around the centre of a computational domain whose dimensions are considerably larger than the chord-length of the airfoil. The NACA 2412 airfoil was designed and printed as three separate parts.Keywords: Reynolds-averaged Navier-Stokes, simpleFoam From the literature the stall angle occurs between 10o and 16o. $FOAM_TUTORIALS/incompressible/simpleFoam/airFoil2D In this project, the aim is to study the behavior of a NACA 0012 airfoil at a Reynolds number of 50,000, at various angles of attack ranging from 0o to 16o. Two airfoil sections, NACA 0012 and NACA 0025, of 7.39 cm chord length (i.e., leading to trailing edge dimension) were shaped from curved laminated Lauan blanks which had the grain oriented along the blade arc.Newtonian, single-phase, incompressible, non-reacting.The airfoil has a 8 in chord, extended the full width of the tunnel and had several small streamers taped to the upper surface in order to visualize the flow3. ![]() See the resources section for additional data files A NACA 0015 airfoil, made of composite materials and mounted in the center of the test section was used for this experiment.References: Gregory-O'Reilly (1970), McCroskey (1987), Ladson (1988), Spalart-Allmaras (1994), and Krist et al.
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