The difference is attributed to the intermittent nature of the flow reversal. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers. Click on an airfoil image to display a larger preview picture. There is considerable disparity between extent of flow reversal in the wake as measured by pressure and hot-film probes. In this project, we selected a NACA 2412 slow-speed Airfoil with maximum thickness 12 (at 30 chord line) from the leading edge, and maximum camber 2 at 40 chord line. Airfoil database search (NACA 4 digit) Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Boundary layer displacement thickness, momentum thickness, and shape factor agree well with theory up to the point of separation. Pressure distributions and separation point locations show good agreement with theory for the two layer angles of attack. Extensive force, pressure, tuft survey, hot-film survey, local skin friction, and boundary layer data are also included. Pre- and post-separated velocity and pressure survey results over the airfoil and in the associated wake are presented. For optimization purposes, control points of the cubic B-spline are used for modeling the airfoil as analyses are done with Qblade. Data for the NACA sections has been derived from the book Theory of Wing Sections, by Abbott and Von Doenhoff. This app queries an aerodynamic database of NACA 4 digits, 5 digits, 6 series, and NASA supercritical airfoils. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 12.4 degrees, 14.4 degrees, and 16.4 degrees. Get airfoil characteristics from an experimental database. Experimental Studies of Flow Separation of the NACA 2412 Airfoil at Low Speeds Wind tunnel tests have been conducted on an NACA 2412 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Get airfoil characteristics from an experimental database.
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