NACA 6-Series (NLF) Airfoil Airfoils with emphasis on maximizing Natural Laminar Flow (NLF). NACA Airfoil Charts Every NACA airfoil has two charts to present the lift, drag, and moment coefficient data for the airfoil. The airfoils investigated in this study include NACA 0009, NACA 0012 (conventional and reversed configuration), Clark-Y, flat plate airfoils (1, 3, and 5% thickness), and thin cambered plates (3, 6, and 9% camber). number airfoil data. was utilized. 1 2. In general, it is 8 1 - 0 . The NACA 0015 is a symmetrical airfoil with a 15% thickness to chord ratio. Figure 6.47 shows the evolution of z-vorticity contour (left) of the flow and upper surface skin friction coefficient (right) of the NACA 0012 airfoil predicted by the Mesh-B (fine mesh) case with Gieseking’s model during upstroke pitching, starting from angle of attack of 14.38° and continuing to 25.98°. Validating the NACA 2412 airfoil is a time-dependent proce ss, so it should be modeled with a time-dependent simulation. If the airfoil is placed at some angle of attack in a moving fluid, it will create some drag. Downstream of the 2 0 0 . The NACA 4 digit and 5 digit airfoils were created by superimposing a simple meanline shape with a thickness distribution that was obtained by fitting a couple of popular airfoils of the time: +- y = (t/0.2) * (.2969*x 0.5 - .126*x - .3537*x 2 + .2843*x 3 - .1015*x 4 ) The coefficient of drag is calculated which is given in Table 3. This valve allows measurements to be taken of each pressure tap individually and progressively incremented one by one through the computer. We ran a steady-state and a transien t simulation for 0 and 10 8 AoA. Since the airfoil is placed at 4° angle of attack, it generates drag. From Summary: "The historical development of NACA airfoils is briefly reviewed. ConclusionAnalysis of NACA 23012 and NACA 2415 airfoil … Click on an airfoil image to display a larger preview picture. In Chapter 3, a discussion of all the airfoils is given first; then the figures (airfoil plots and performance data) are presented in Chapter 4. The airfoil is described using six digits in the following sequence: 1. 4 0 . 2 0 . New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The discussion is organized according to the application (i.e., free flight model airfoils are first discussed, then F3B airfoils … Figure 1: NACA 0015 Airfoil Cross-section with Pressure Taps. AN EXPERIMENTAL LOW REYNOLDS NUMBER COMPARISON OF A WORTMA" FX67-Kl70 AIRFOIL, A NACA 0012 AIRFOIL, AND A NACA 64-210 AIRFOIL IN SIMULATED HEAVY RAIN ABSTRACT Wind tunnel experiments were conducted on Wortmann FX67-Kl70, NACA 0012, and NACA 64-210 airfoils at rain rates of 1000 mm/hr and Reynolds numbers of 310,000 to compare the aerodynamic performance degradation of the airfoils … INTRODUCTIONThis experiment analyzes the NACA 0015 airfoil in a low speed wind tunnel at varying angles of attack. The number "6" indicating the series (NACA 6-Series NLF Airfoil). Symmetric airfoils are used in many applications including aircraft vertical stabilizers, submarine fins, rotary and some fixed wings. Airfoils were examined for lift and drag performance as well as surface pressure and flow field characteristics. 6 0 . The NACA 0012 airfoil is symmetrical; the 00 indicates that it has no camber. One digit describing the distance of the minimum pressure area in tens of percent of chord. The locations of these pressure taps are shown below in Figure 1. There are links to the original airfoil source and dat file and the details … data acquisition computer. The first chart will have curves of lift coefficient versus angle of attack at various Reynolds numbers and curves of moment coefficient at the quarter chord point versus angle of attack at various Reynolds numbers. The 12 indicates that the airfoil has a 12% thickness to chord length ratio; it is 12% as thick as it is long. Airfoil database search (NACA 6 series) Search the 1638 airfoils available in the databases filtering by name, thickness and camber.